The effect of transition wires on the pressure distribution over a N.A.C.A. 63A215 aerofoil section

LIEGTUIi :i anaalstraat 10 - DELFT

7 NOV. 1956

THE COLLEGE OF AERONAUTICS

CRANFIELD

THE EFFECT OF TRANSITION WIRES ON THE

PRESSURE DISTRIBUTION OVER A N.A.C.A.

63A2I5 AEROFOIL SECTION

by

Kanaalstraat 10 - DELFT TECmTICAL NOTE N0.UI "FE.6RUAP.Y; 1956.

H E C O L L E G E O P A E R O N A U T I C S C R A N F I E L D

The effoct of transition v/ires on the pressure distri"bution over a N.A.C.A, G3A215 aor'ofoil section.

-hy-K. D. Harris, B, Sc. (Eng. ), D.C.Ae., A.P.R.Ae.S.

SUMMARY

pressure distrihutions have heen measured over the su:.?face of a N.A.C.A. 63A215 aerofoil section to determine the effect of transition wires on the lift and pitching moment characteristics. Tnese festSj, which were made at Reynolds numbers of 3 x 10^ and 8 X 10-^., showed that with transition left free laminar separation, followed hy turbulent re-attachment,

occurred at about 60Z chord at low incidences. At miSdium incid8n.ce the position of laminar separation and turbulent re-attachment moved rapidly forward giving rise to klnlvs or non-linearities in the lift curve.

The addition of transition Jirires at 27-^-^ chord eliminated the lamj.nar separation at lov/ incidences and thereby caused the lift curve to become more nearly linear. However, the v/ires resulted in a reduction in the lift-curve slope at the design C,, and a redaction

in CT „.,. " ^

Transition vvires at 8/i, luC or 1% chord were fo^ond

to have very adverse effects on the aerofoil characteristics. In particular the lift curves were made very non-linear,

and CT,_^^ was reduced. The non-linearity Y/as caused by

•'•'ma X

sudden changes in the boundary layer with change of incidence, PDF

CONTENTS Page Summary 1. Notation 2. Introduction 3. Description of Apparatus k. Details of Test 5- Presentation of Results 6. Discussion 7. Conclusions 8. Acknowle dgement s 9. References - APPENDIX Tables

I Ordinates of N.A.C.A. 63A2-15 II Lift and pitching moment results III Pressure distributions at R = 3 x 10

(i) transition free ^

fii) transition wires at 27|-/{ chord (iii)transition wires at 8J|' chord (iv) transition wires at 14.% chord

(v) transition wires at 1% chord

IV Pressure distributions at R lAe 8 x 10

(i) transition free ^

(ii) transition v;ires at 2Ji/o chord

fiii)transition wires at 8% chord

fiv) transition ?/ires at l\% chord

(v) transition wires at 1^ chord

k

6

6

7

8

9

15 16 16

Diagrams and Figures

Diagram of model

Lift characteristics

Pitching moment characteristics (R = 3 x 10 )

Pitching moment characteristics (R ^ 8 x 10 )

Upper surface pressure distributions

(a) a^ = -2°

(b) a^ = 6°

(c) a^ = 10°

(d)

a ^ =

11).°

Comparison of pressure distributions near the

stall at two values of the Reynolds number.

The approximate chordwise positions of laminar

separation, turbulent re-attachment and turbulent

separation.

Comparison of lift-curve slopes for test section

(N.A.C.A. 63A215) with N.A. C. A. section 6i+A21 2.

Notation

chord

chordwise force coefficient lift coefficient

lift coefficient uncorrected for tunnel interference

pitching moment coefficient measured about the quarter chord point

pitching moment coefficient uncorrected for tunnel interference

normal force coefficient pressure coefficient

effective height of working section

distance of the aerodynamic centre aft of the leading edge measured as a fraction of the chord c.

static pressure on aerofoil surface atmospheric pressure

static pressure at entry to wind tunnel contraction dynamic pressure

Reynolds number based on chord c oVc

^.

Axes xy are taken with origin at the leading edge, the X-axis being coincident with the chord line and the y-axis being perpendicular to the x-axis.

a = wing incidence (corrected for tunnel interference) a-, = geometric wing incidence

|j, = coefficient of viscosity of the air p = density of the air

2. Introduction

The tests described in this report v;ere undertaken as a result of a request that the College should make a series of stability and control tests on a wind tunnel model of an aeroplane having a v/ing of aspect ratio 20. Since the largest tunnel available for these tests was

one with a vi^orking section 3i: feet in diameter, and a

top speed of about 1L|.0 feet per second, it followed that the Reynolds number of the tip section of the model v;ing would only be about 1 x 10^. Concern was felt lest the

results obtained at such a low Reynolds number might differ appreciably from the flight characteristics at the full scale Reynolds number of about 2 x 10°. It was therefore decided to investigate the characteristics

of the tip section over the v/idest possible range of Reynolds number available in the v/ind tunnel to see if by the use of transition wires the characteristics at R = 1 X 10-^ could be made similar to the characteristics at R = 2 X 10°. To obtain sufficiently detailed

information it was decided to pressure plot a relatively large model of the tip section. The results obtained are of considerable interest^ and because of the dearth of published information on pressure distributions with and without transition vi^ires it was felt that some use might be served by publishing the present results. It

should be pointed out however that the tunnel interference corrections v;hich had to be applied were large and

somewhat approximate owing to the fact that no published

correction data is available for the particular configuration of model and tunnel that was used.

3- Description of Apparatus

The model, which is illustrated in Figure (1),

consisted of a rectangular wing of chord 1 foot and span 3 feet, with oval shaped endplates attached to the tips. The aerofoil section was N.A.C.A. 63A215, the ordinates of which are given in Table I.

Spanwise pressure tubes v/ere let into the upper and lower surfaces of the model at the following chordv/ise positions

:-^ = 0, 0.025, 0.05, 0.075» 0.10, and thereafter at intervals of O.O5 back to x/c = O.80.

The model was constructed of wood, and, as originally supplied, the aerofoil section ?/as far from accurate.

The model was therefore improved by modifying the section over the mid portion of the span where the pressure holes were situated.

The tests were made in the College of Aeronautics 'No. 2 Vifind Tunnel'. This tunnel has a circular-section, open-jet working section of diameter 3-2' feet, and a top speed of about II4.0 feet per second.

The incidence of the model relative to the horizontal was measured by means of a sensitive inclinometer, and

the pressure distributions were measured on a tilting multi-tube manometer containing methylated spirits.

k' Details of Test

Pressure distribution measurements were made at two wind speeds. These speeds were chosen to give the

greatest practicable range of Reynolds number. The lower speed, v/hich was determined by considerations of the accuracy of the observed results, was /+6. 8 feet per second. The upper speed, which was chosen as the maximum available tunnel speed, varied from about 132 feet per second at low incidence to about II5 feet per second at the maximum test incidence. The low speed tests gave a Reynolds number of 3 x 10^ based on the wing chord of

1 foot, v/hereas the high speed tests gave a mean Reynolds number of about 8 x 1o5.

To obtain a high degree of repeatability in setting the incidence an inclinometer was used in preference to the incidence telescope. Use of the inclinometer

necessitated stopping the tunnel each time the incidence was changed. This may have influenced the results

obtained at the higher incidences, but this v/as not considered important because the stalling behaviour of the aerofoil was not the object of investigation.

Tests were made with transition free and with transition wires attached to both the upper and lower surfaces at

The diameter of the wire used was 0.028" ; attachment to the wing surface v/as by means of chordwise strips of adhesive tape.

The pressure distributions were measured on a tilting multi-tube manometer. The static pressure in the working section was assumed to be exactly atmospheric. The dynamic pressure was measured by a static tapping taken from the entry to the contraction. Calibration of the empty tunnel shows that the dynamic pressure

q. (= ^pV^) is given by the formula

:-a = (Pc -

PA)-However, as described in the Appendix, it v/as found that with the model in the tunnel the tunnel calibration

factor was not a constant, and the following approximate formula was deduced

:-q = (1 + 0.05 C£)(p^-p^).

Presentation of results 5.1 C distributions

The Cp distributions are given in Tables III and IV. A few selected distributions are plotted in Figures (5) and (6). It should be noted that no corrections for tunnel interference effects have been applied to either the tabulated or plotted distributions.

5.2 Lift and pitching moment results

The lift and pitching moment coefficients are given in Table II. In Figure (2) C^ is plotted against a,

and in Figures (3) and {l\.) C^^ /, is plotted against C^.

These results have all been fully corrected by the methods outlined in the Appendix.

For the reasons given in the Appendix no drag results are given.

5.3 Lift-curve slope and aerodynamic centre In most of the test configurations the C-r '^ a curves were not linear. The lift-curve

slopes quoted below have therefore been evaluated at the section design CT of 0.2. The aerodynamic centre positions have likewise been evaluated at a CT of 0.2.

In certain cases reliable values of lift-curve slope and aerodynamic centre are not obtainable from the measured results. Where this is the case a question mark (?) has been placed in the appropriate space.

D i s t a n c e of t r a n s i t i o n w i r e a f t of l e a d i n g e d g e ( x / c ) No w i r e s 0 . 2 7 5 0 . 0 8 0.0i+ 0 . 0 1 dCr / d a R i^0^

3

5.1+ 5 - 0 5 . 0 k-k 5 . 0 8 5-k 5 . 1 5 . 0 ? l + . 7 ( 5 ) ^'n r R i 10^ 3 0 . 2 U 5 0 . 2 2 5 0 . 2 2 5 0 . 220 0 . 250 8 0.2Z+5 0 . 2 3 0 0 . 2 4 0 0 . 2 3 0 ?

The lift-curve slopes have been quoted to the nearest 0.1, and the aerodynamic centre positions to

the nearest O.OO5. It is considered that whilst the absolute values may not be accurate to within these limits (on account of the uncertain tunnel interference corrections and the lack of sufficient pressure holes) the quoted values are repeatable to v/lthin these limits.

6. Discussion

6.1 Lift characteristics (Figure 2)

The fully corrected lift results are plotted in Figure (2), where, to facilitate comparison of the results, the linear lift curve obtained at R = 3 x 10 with transition wires at 27-g% of the chord has been plotted against each set of results*.

This reference curve extends beyond the incidence

Generally speaking it will be seen that the lift curves are appreciably more linear with the transition wires at 27>%chord than with no transition wires.

However, wires at 8 % l\X or l^f chord make the lift

characteristics progressively less linear. Those features are all more marked at the lower Reynolds number of 3 x 10^.

From the Table in Section 5 it will be seen that

the addition of the transition wires results in a reduction in the lift-curve slope at the design C-^. In general

the reduction in lift-curve slope increases as the

wires are moved towards the leading edge. An exception to this behaviour occurs at the lower Reynolds number when the transition wire is brought right forv/ard to 1% chord. This is due to the fact that the wire is then in a strongly favourable pressure gradient, and the Reynolds number of the boundary layer (based on its thickness) is small. As a result of this the wire causes some thickening of the laminar boundary layer but does not cause transition to turbulent flow.

The kinks and non-linearities in the lift curves are caused by changes in the boundary layers with change of incidence. These changes are discussed in subsections

3, k and 5 of the present Section.

6.2 Pitching moment characteristics (Figures 3 and i|)

The C ~ CT curves plotted in Figures 3 and I4. are

m L

moderately linear except at incidences where the lift curves become markedly non-linear. The results

tabulated in Section 5 show that at the design C-p the aerodynamic centre of the section is at 24.5%

of the chord with transition free. The addition of

transition v/ires at 27^7„ chord moves the aerodynamic

centre forward. This is due to the thickening of the boundary layer aft of the wires. As the v/ires are moved forward towards the leading edge the tendency is for the aerodynamic centre to move slightly fiorther forward. The opposite effect occurs at the lower Reynolds number when the VYire is moved forward to the foremost position of 1% chord. This is due to the fact that at low incidences the wire does not cause transition to turbulence and so does not cause any appreciable

6. 3 The effect of transition Y/ires on the upper

surface pressure "distributions. (Figures 5a to 5d) The pressure distributions plotted in Figures 5a to 5d are confined to thep-upper surface and to a

Reynolds number of 3 x 10 . This is because the main points of interest are confined to the upper surface, and because the results at the higher Reynolds number are very similar to those at the lov/er value.

Figure 5a (o.^ = -2°)

Referring first to the pressure distributions at

(iQ = -2° it will bé seen that with no transition wires

there is a short region of approximately constant pressure at about 6o% of the chord and that this is followed by a fairly rapid rise in pressure. This feature is

eliminated with transition wires at 27^% and with wires at 8% chord, but it re-appears when the wires are moved forward to i+% or 1^ chord.

The explanation of this phenomenon is well known. The region of approximately constant pressure coincides with a region of laminar separation, v^hilst the region

of rapid pressure recovery coincides with a region in which the boundary layer changes from laminar to

turbulent and re-attaches to the surface as a turbulent layer. In this region the boundary layer displacement thickness decreases rapidly, and it is this which causes the rapid increase of static pressure. Laminar

separations of this type have been studied experimentally by Bursnall and Loftin(2) j and Owen and Klanfer(3) have

shown that this type of bubble falls into the category termed 'short bubbles'.

Figure 5b (a^^ = 6°)

At aQ = 6° the region of laminar separation is still at about the same chordwise position as at a^ = -2 , but it appears that transition to turbulence and

re-attachment takes place more rapidly after the onset of separation. The addition of the transition wires evidently causes transition to turbulent flow close to the \7ire

Figure 5c (a_ = 10 )

At a^ = 10° the region of natural transition to turbulent flow has moved forv/ard close to the leading edge. With no transition wires it appears that there is probably a short region of laminar separation at about 5^ chord follov/ed by almost immediate transition and re-attachment.

Whilst the form of the pressure distribution curves (except in the immediate vicinity of the wires) is very similar for all positions of the transition wires it can be seen that over the forward 40% of the chord there is

a distinct reduction of the suction with the v/ires

attached to the aerofoil, and this tends to increase as the v;ire is moved towards the leading edge. The

explanation of this is that the wire causes the turbulent boundary layer downstream of the wire to be thickened. Reference to Figure 5c will show that the reduced suctions

over the forv/ard part of the upper surface give rise to reduced values of the lift coefficient.

Figure 5d (a^ = 14°)

At ttp = 14° the boundary layer is turbulent from near the leading edge irrespective of the position of

the transition v/ire. It is evident though that as the wire is moved towards the leading edge there is a gradual

increase in the extent of the separated flow near the trailing edge. At both values of the Reynolds number and for all positions of the transition wire the stall is caused by a turbulent separation starting at the trailing edge. The effect of the addition of a transition wire is therefore to decrease the stalling value of the lift coefficient. This is clearly shown in Figure 2 where it will be seen that CT falls progressively as the

•^max J:- D

transition wire is moved towards the leading edge. 6.4 The effect of Reynolds number on the pressure

distribution near the stall.

Figure 6 compares the pressure distributions measured

at a„ = 18° at Reynolds numbers of 3 x 10^ and 7-4 x 10^,

with transition free.

layer separates on the upper surface at about 6o% of the chord for both values of the Reynolds number.

The other feature of interest is that whilst over the v/hole of the lower surface and over much of the upper

surface the pressure distributions are almost identical there is a region from the leading edge back to about 10/^ chord on the upper surface v/here the distributions differ quite markedly. This is probably associated v/ith

differences in the transition of the boundary layer from laminar to turbulent. At the lov/er Reynolds number there is fairly certain evidence that there is a region of laminar separation at about 4/o chord follovt^ed by

turbulent re-attachment at about 6% chord. At the

higher Reynolds number there may be a somewhat similar behaviour, but if this is so the transition to turbulence probably takes place very shortly aft of the position of

separation .

6.5 The approximate chordwise positions of laminar separation, turbulent re-attachment and turbulent separation on the upper surface.

In Figure 7 an attempt has been made to indicate

the approximate chordwise positions of laminar separation, turbulent re-attachment and turbulent separation on the upper surface over the full C-^ range. These curves are for transition free. This plot is necessarily

approximate as the positions at vïhich these flow changes take place have had to be deduced from the pressure

distributions. The curves are particularly approximate in the range where the position of transition is varying rapidly v/ith change of lift coefficient. Indeed, although tentative curves have been plotted indicating the positions

This statement is based on theoretical reasoning rather than on the measured pressure distribution curves.

Theory (see Ref.5, p.124) predicts that the position of laminar separation is independent of Reynolds number

(provided the pressure distribution up to the point of separation is itself independent of Reynolds number). It is furthermore a v/ell knovm fact that the position of transition from laminar to turbulent flow in the boundary layer moves towards the front stagnation point

of laminar separation and turbulent re-attachment the experimental results are not sufficient to assert that separation definitely takes place in this regime.

It is interesting to note that the regimes where rapid changes of the boundary layer occur correspond with the regimes where the lift curves of Figure 2 are kinked or distinctly non-linear,

S.S A comparison of the lift-curve slopes of the

test section (N.A.C.A. 63A215) and N. A. C. A. section 64A212.

In Figure 8 the lift-curve slopes obtained from the present series of tests are compared with

measurements made by the N.A.C.A. (4) on a slightly different section (N.A.C.A. 64A212). The latter measurements, which were made over az-Reynolds number range varying from 7 x 10^ to 9 x 10 , enable some useful deductions to be drawn. In the first place

it will be seen that at R = 3 x 10^ the results of the present experiment agree quite closely with the N.A.C.A. results. Because of the similarity of the two aerofoil sections it would appear reasonable to assume that the

variation of lift-curve slope with Reynolds nxmber will

be the same for the two sections, g Assuming this to be the case we see that at R = 2 x 10 , which corresponds approximately to the full scale Reynolds number of the

tip section of the project, the lift curve slope is ^

about 5'5 {5)- From the present tests at R = 3 x 10-^

the lift-curve slope is 5.4 with transition free and 5.0 with transition wires at 27-|-% chord. This suggests that the lov/ incidence characteristics of the complete aircraft will best be simulated by a wind tunnel model having free transition on the virings. On the other hand, for tests at medium to high incidence it might be desirable to use a transition VYire at about 30^ chord to eliminate the kinks in the lift curve which are associated with the

rapid forward movement of the transition point. The results of the test shovi^ that for Reynolds numbers less than 0. 8 x 10° laminar separation does not

occur until aft of 30% chord in the low incidence range.

Thus, if for any reason it v/as deemed advisable to use transition wires for low incid-ence tests it might be

would probably lead to a slightly smaller loss in the lift-curve slope due to the addition of the wires. In addition some slight reduction in the loss of lift-curve slope might be achieved by the use of a smaller diameter wire.

7. Conclusions

From the foregoing discussion it is concluded that for low incidence tests on complete models having a

N.A.C.A. 63A215 section the best results will be obtained with transition left free on the wings. However, to avoid kinks in the lift and pitching moment curves it may be desirable to use transition wires on the wings for tests at medium to high incidence. The present tests show that such wires should be placed at least

as far back as 30% of the chord. It is also tentatively suggested that if transition wires are used for lov/

incidence tests some slight benefit might accrue from placing these wires as far aft as 50/^ chord.

At lov; values of incidence laminar separation occurs on the plain vising at about 6o% of the chord on the upper surface and this is follo?/ed by turbulent

re-attachment a little further downstream. At moderate incidence the region of transition from laminar to

turbulent flovY moves rapidly forvmrd toY^ards the leading edge. This rapid movement is associated Tvith kinks or non-linearities in the lift curves.

At high values of incidence there appears to be a short separation bubble on the upper surface near the leading edge. The available measurements are

however not sufficiently detailed for any firm conclusions to be draY/n regarding the nature of the boundary layer at slightly lovi;er incidences except to say, as stated previously^ that the position of transition moves rapidly forv/ards with increase of incidence in this incidence range.

The stall occurs through the gradual groYt^th of a turbulent separation v/hich starts at the trailing edge at a Cj of about 0.9 and spreads forY/ard with increase of incidence.

Transition wires at 27-^/^ chord eliminate the

laminar separation at lovv incidences and thereby cause the C]^/«^ a curves to become more linear. Hovi^ever, the Y/ires result in a red-uction in the lift-curve slope at loYiT incidence and a reduction in CT,

•'-'max

Transition v/ires near the leading edge generally

have a very adverse effect on the aerofoil characteristics At low incidences they do not necessarily cause transition to turbulence, whilst at medium incidences they cause

the point of transition to move sudd.enly forY^ard giving rise to kinks in the C T '^ a curves. Also, by thickening the boundary layer at high Incidence, they cause a

reduction in the CT of the section.

-Umax 8. AcknoYif lodgement s

AcknoY\rledgement i s d.ue t o Mr. and Mrs. Hanning-Lee v/ho prompted t h i s work and. s u p p l i e d t h e model. The a u t h o r would a l s o l i k e t o thank Mr. G. G. Appleby and Mr. P. E. W. Sharman v;rho h e l p e d t o conduct t h e

e x p e r i m e n t a l work.

9. References

1. PanJchurst. R. C. and Holder, D.W. Wind Tunnel Technique.

Pitman. 2. Bursnall,W.J. and Loftin, K.L,

Experimental investigation of localised

regions of laminar boundary layer separation. N.A, C.A. T.N, 2338.

3. Owen, P. R. and Klanfer, L,

On the laminar boundary layer separation from the leading edge of a thin aerofoil.

4. Lof tin, K.L. and Smith, H. A.

Aerodynamic characteristics of 15 N.A,C.A. airfoil sectipns at seven Reynolds numbers from 0. 7 X 10^^ to 9.0 x 10°.

N. A, C,A. T.N. 1945 5. Goldstein, S. (Editor)

Modern Developments in Fluid Dynamics (Vol. I)

Oxford University Press,

APPENDIX

Evaluation of uncorrected lift and pitching moment coefficients.

The non-dimensional pressure distributions were plotted against x/c and y/c and integrated by means of an integrator to find the coefficients C„, C„ and C^

JM C ^""l /

The uncorrected lift coefficient C' Y/as then '^ calculated by means of the formula

C£ = G^ cos a^ - C^ sin a^.

Owing to the relatively few pressure holes near the leading edge and to the lack of pressure holes over the rear 20% of the chord the chordwise force coefficient CQ could be determined only very approximately. For this reason no attempt v/as made to evaluate the drag of the aerofoil. (In any case the drag obtained vYould have been purely the form drag since no measurements of the

skin friction or overall drag Y;ere made. ) Blockage correction

From Reference 1 pp. 334 and 335 the blockage . ^ correction at zero lift is found to be approximately T-^ on the velocity. Since this is Yi^ell Y/ithin the ^ limits of experimental accuracy this correction has been neglected. No published information is available

regarding the blockage at other than zero lift, but it Yi/as observed that the maximum obtainable tunnel speed

Kanaalstraat 10 - DELFT

18

-feil appreciably as the incidence was increased. At the same time it Y/as observed that the apparent stagnation pressure coefficient rose from 1,00 at a^ = 0° to about

1.05 at a-., = 16°, This indicated that the tunnel calibration factor, which v/as known to be 1.00 for the working section empty, must have risen from 1.,00 at low Cf^ to about 1.05 at a C£ of about 1.0. Evidence of

the variation of the tunnel calibration factor at

intermediate values of C-^ was not obtained and it vras

therefore assuined that the factor Y/ould vary linearly Y/ith C-^, Accordingly the dynam.ic pressure q v/as assumed to be given by the formula

q = (1 +0.05 C£)(p^- p^).

Lift and pitching moment corrections for tunnel Interference effects.

The corrections to be applied to the observed lift and pitching moment results for tunnel interference

effects are necessarily approximate ov/ing to the fact that :

-(i) the tests were made in a circular-section,

open-jet tunnel, and

(ii) the model v/as fitted Y/ith finite area end-plates.

Tunnel interference corrections have not been computed for the above case. The nearest case for which corrections have been published is the case of two-dimensional tests* in a recoangular-section, open-jet tunnel. In the absence of any better information it has been assumed that the corrections to be applied to the mid span station of the model in this test are the same as the corrections to be applied to the case for the rectangular-section, open-jet tunnel, except that the effective height (h) of the circular section tunnel is to be taken as the mean height over the span of the m.odel, i.e. h = 3.1 feet,

With the above approximation the tunnel interference corrections as given in Reference 1 are (in the present

notation) :- . 24 (hj ^L 2 °L = C' * a. = dr 48 Vhj l^ L ^ m^,) k[n} I o 9 ^4 2 . . 2 C = C * -^^' •" \ C ' )

Substituting for c and h these formulae become :-c^ = 1.0427 C£

a = a., - 0.0873 c; - 0.0272 C' _{U- i i m}

'A

c^ = c ' - 0.0103 c '

my^ my^^ L

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Lift and Pitching Moment Results R

a°

- 2 . 0 9 - 0 . 6 4 0 . 7 4 2 . 0 7 3 . 4 0 4 . 7 4 6 . 1 0 7 . 7 7 9 . 3 2 1 1 . 0 5 1 2 . 7 8 = 3 X 1C CL 0 . 0 2 9 0 . 1 4 3 0 . 2 6 9 0 . 4 0 5 0 . 5 3 7 0 . 6 6 5 0 . 7 8 9 0 . 8 5 3 0 . 9 3 6 0 . 9 9 0 1.040 F r e e T r a n s i t i o n - 0 . 0 3 5 - 0 . 0 3 2 - 0 . 0 3 3 - 0 . 0 3 9 - 0 . 0 3 2 - 0 . 0 2 8 - 0 , 0 3 7 - 0 . 0 2 3 - 0 . 0 3 1 - 0 . 0 0 7 - 0 . 0 0 4 R

a°

- 2 . 0 4 - 0 . 6 5 0 . 6 9 2 . 0 4 3 . 4 9 4 . 8 8 6 . 4 6 7 . 8 5 9 . 3 5 1 1 , 1 5 1 2 . 7 3 ^ 8 X 1 0 ^

°L

0 . 0 1 9 0 . 1 4 5 0 . 2 3 0 0 . 4 0 8 O . 5 I 8 0 . 6 3 8 0 . 7 3 9 0 . 8 3 6 0 . 9 3 1 0 , 9 6 9 1.048 m - 0 » 0 3 3 - 0 . 0 2 9 - 0 . 0 3 5 - 0 , 0 3 1 - 0 . 0 2 6 - 0 , 0 1 8 ~0o022 - 0 . 0 1 8 - 0 . 0 1 9 - 0 , 0 0 3 - 0 . 0 1 7

0.028" Diameter Transition Wires at 27.5]!^ Chord on Upper and Lower Surfaces

R 0 a - 2 , 10 - 0 , 6 9 0 . 6 8 2 . 0 7 3 . 4 7 4 . 9 0 6 . 2 5 7 . 7 6 9 . 3 3 1 1 . 2 4 1 3 . 1 4 = 3 X 1C «L 0 , 0 3 2 0 , 1 5 3 0 , 2 8 0 0 . 4 0 1 0 . 5 2 2 0 . 6 3 4 0 . 7 5 9 0 . 8 5 4 0 . 9 3 6 0 . 9 5 3 0 , 9 7 3 )5 ^m - 0 . 0 4 0 - 0 . 0 3 7 - 0 . 0 3 7 - 0 . 0 3 5 - 0 . 0 2 8 - 0 . 0 2 8 - 0 . 0 3 3 - 0 . 0 2 1 - 0 . 0 2 0 - 0 , 0 0 9 - 0 . 0 1 2 R # : 8 X 1C a - 2 , 0 1 - 0 , 5 9 0 , 7 6 2 . 1 3 3 . 5 5 -6 . 3 7 -9 . 4 2 1 1 . 0 8 — ^L 0 . 0 1 3 0 . 1 3 2 0 . 2 6 5 0 , 3 8 1 0 , 5 0 9 -0 . 7 3 8 -0 , 9 1 8 0 . 9 8 4 — )5 ^m - 0 . 0 3 4 - 0 . 0 3 3 ...0.029 - 0 . 0 2 9 - 0 . 0 2 6 -- 0 . 0 2 2 -- 0 . 0 0 9 - 0 . 0 1 0 *>

0 . 0 1 5 " D i a m e t e r T r a n s i t i o n W i r e s a t 8/^ Chord j on U p p e r a n d Lower S u r f a c e s ' 1 R = 3 X 10^ 1 0 • ^ - 2 . 0 4 0 , 7 2

1 3.61

1 6.61

i 9 . 5 0 1 1 1 . 13 CT 1 0.^ L ! m 0 . 0 1 9 0 . 2 7 3 0 . 4 9 6 0 . 6 9 3 0 , 9 0 4 0 . 9 7 3 - 0 . 0 3 8 - 0 . 0 3 1 - 0 . 0 2 7 - 0 . 0 2 5 - 0 . 0 1 6 - 0 . 0 2 0 R = 8 X 10^ 0 i n - 2 . 0 8 1 - 0 . 0 0 8 0 . 7 6 1 0 . 2 6 3 3 . 6 6 1 0 . 4 8 6 6 . 6 2 ! 0 . 6 7 8 9 . 5 6 j 0 . 8 9 2 1 1 . 2 8 j 0 . 9 4 7

Cm J

- O . Ö 3 4 j - 0 , 0 3 8 j

-0,029 1

- 0 , 0 1 6 - 0 . 0 0 4 - 0 . 0 0 7 0 , 0 1 5 " D i a m e t e r T r a n s i t i o n W i r e s a t i ^ Chord 1 on U p p e r a n d LoY/er S u r f a c e s | R = 3 X 10^ a °

1 -2.18

0 . 7 2 3 . 6 3 6 . 5 8 9 . 6 2 1 1 . 3 7

L i 1

0 . 0 4 7 0 , 2 7 3 0 . 4 9 3 0 , 6 9 6 0 , 8 7 3 0 . 9 3 0 Cm - 0 . 0 4 7 - 0 . 0 4 1 - 0 . 0 3 2 - 0 . 0 2 5 - 0 . 0 1 4 - 0 , 0 2 1 R 4= 8 X 10^ 1 0 a - 2 . 0 0 0 . 7 3 3 . 5 8 6 . 6 1 9 , 8 0 1 1 . 4 5 CL - 0 , 0 1 0 0 . 2 7 1 0 , 5 0 2 0 . 6 9 2 0 . 8 9 6 0 . 9 1 4

Cm 1

-0.037 1

-0.025 1

- 0 . 0 2 3 - 0 . 0 1 7 - 0 . 0 0 6 - 0 . 0 0 7 1 0 . 0 1 5 " D i a m e t e r T r a n s i t i o n Y / i r e s a t 1^ Chord j 1 on U p p e r a n d Lower S u r f a c e s i R 0 a r - 2 . 2 1 0 . 5 9 3 . 5 7 6 . 8 0 9 . 6 5 1 1 . 4 9 = 3 X 1 0 ^

^L 1

0 , 0 5 4 0 , 3 0 0 0 . 5 0 4 0 . 6 5 3 0 . 8 7 5 0 , 9 0 5 % - 0 . 0 3 6 - 0 . 0 3 7 - 0 , 0 3 5 - 0 , 0 3 3 - 0 , 0 1 7 - 0 . 0 1 8 R # 8 X 10^ ! 0 a - 2 . 0 8 0 , 7 7 3 . 7 3 6 , 7 4 9 . 8 2 1 1 . 5 5 .... i _ _ „ . 0 . 0 2 7 0 . 2 6 4 0 . 4 7 0 0 , 6 6 6 0 , 8 4 3 0 , 8 9 5 ..,_=m. - 0 . 0 3 2 - 0 , 0 3 7 - 0 . 0 2 7 - 0 , 0 1 5 - 0 . 0 0 9 - 0 . 0 0 2

Table I I (concluded)

R = 3 X 10^ T r a n s i t i o n F r e e

x7cr-^^!

L e a d i n g e d g e 0) Ü Co <H f^ cn U 03 P P I i i 1 i t o Co

u

CO CD O 0 . 0 2 5 0 . 0 5 0 0 . 0 7 5 0 . 10 0 . 1 5 0 . 2 0 0 . 2 5 0 . 3 0 0 . 3 5 0.4C 0 . 4 5 0.5Q 0 . 5 5 0 . 6 o 0 . 6 5 0 . 7 0 0 . 7 5 Ö.80 0 . 0 2 5 0 . 0 5 0 0 . 0 7 5 0 . 10

jo. 15

to. 20 10.25 ! Q . 3 O 0 . 4 0 Q.3Q 0 . 6 0 0 . 7 0 0 . 8 0 1 - 2 . 0 9 0 . 8 2 0 . 3 2 0 . 0 2 - 0 . 1 0 - 0 . 2 0 - 0 . 30 - 0 . 39 - 0 . 4 3 - 0 . 4 6 - 0 . 4 6 - 0 . 4 6 - 0 . 4 6 - 0 . 4 1 - 0 . 3 6 - 0 . 3 5 - 0 . 3 2 - 0 . 2 0 0 . 0 0 0 . 0 1 - 0 . 35 - 0 . 4 0 - 0 . 4 2 - 0 . 4 5 - 0 . 4 5 - 0 . 4 1 - 0 . 3 9 - 0 . 39 - 0 . 3 0 - 0 . 2 2 - 0 . 0 8 - 0 . 0 1 0 . 0 2 . - 0 . 6 4 1.00 0 . 0 3 - 0 . 1 6 - 0 . 2 8 - 0 . 3 6 - 0 . 4 3 - 0 . 4 9 - 0 . 5 1 - 0 . 5 3 - 0 . 5 3 - 0 . 5 1 - 0 . 4 9 - 0 . 4 5 - 0 . 4 0 - 0 . 3 9 - 0 . 38 - 0 . 1 4 - 0 . 0 1 0 . 0 1 - 0 . 0 6 - 0 . 1 9 - 0 . 2 5 - 0 . 2 9 - 0 . 32 - 0 . 3 0 • - 0 . 2 9 - 0 . 3 0 - 0 . 2 6 - 0 . 1 7 i - 0 . 0 9 , 0 . 0 0 i 0 . 0 5 0 . 7 4 2 . 0 7 1.02 0 . 9 8 - 0 . 2 1 - 0 . 4 0 - C . 4 9 - 0 . 5 5 - 0 , 5 8 - 0 . 6 3 - 0 . 6 4 - 0 . 6 4 - 0 . 6 3 - 0 . 6 0 - 0 . 5 7 - 0 . 5 2 - 0 . 4 8 - Ü . 4 8 - 0 . 4 5 - 0 . 1 1 - 0 . 0 7 - 0 . 0 3 0 . 1 8 0. 00 - 0 . 1 0 - 0 . 1 7 - 0 . 2 2 - 0 . 2 4 - 0 . 2 5 - 0 . 2 8 - 0 . 2 4 - 0 . 1 5 - 0 . 0 9 - 0 . 0 1 r , 0 3 - 0 , 5 3 - 0 . 6 5 - 0 . 7 0 - 0 . 7 1 - 0 . 7 2 - 0 . 7 6 - 0 . 7 5 - 0 . 7 3 - 0 . 7 0 - 0 . 6 8 - 0 . 6 2 - 0 . 5 7 - 0 . 5 4 - 0 . 5 3 - 0 . 3 2 - 0 . 1 5 - ( " . 0 9 - 0 . 0 5 0 . 4 0 0 . 1 7 " . 0 7 - O . C N 2 - 0 . 12 - 0 . 1 7 - 0 . 13 - 0 . 2 0 - 0 . 1 9 • • ' .• . 1 - 0 . 0 5 0 . 0 0 0 . 0 ^ 3 . 4 0 0 . 7 7 - 0 . 8 7 - 0 . 8 8 - 0 . 9 0 - 0 . 3 9 - 0 . 8 7 - 0 . 8 7 - 0 . 8 3 - 0 . 8 0 - 0 . 7 6 - 0 . 7 2 - 0 . 6 8 - 0 . 6 3 - 0 . 6 0 - 0 . 5 8 - 0 . 2 3 - 0 . 19 - 0 . 1 1 -.-^.06 0 . 6 0 0 . 3 6 0 . 2 2 ^•.13 0 . 0 0 - 0 . 0 7 - 0 . 08 - 0 . 12 - ^ . 12 - 0 . - 6 - 0 . 0 0 0. 02 0 . 0 6

4.74

0 . 3 3 - 1 . 2 5 - 1 . 1 7 - 1 . 1 3 - 1 . 0 8 - 1 . 0 0 - 0 . 9 8 - 0 . 9 3 - 0 . 3 8 - 0 . 8 3 - 0 . 7 8 - 0 . 7 4 - 0 . 70 - 0 . 6 6 - 0 . 4 1 - 0 . 2 8 - 0 . 2 2 - 0 . 1 5 - - - . 0 8 0 . 7 3 0 . 3 5 •".25 0 . 10 0 . 0 2 - 0 . 0 0 - 0 . 0 6 - 0 . 0 8 0 . 0 0 0 . 0 2 0 . 0 6 0 . 10 6 . 1 0 - 0 . 2 5 - 1 . 6 4 -1..'43 - 1 . 3 7 - 1 . 2 9 - 1 . 1 7 - 1 . 1 0 - 1 . 0 4 - 0 . 9 9 - 0 . 9 2 - 0 - 8 8 - 0 . 8 0 - 0 . 6 9 - 0 . 5 7 - 0 . 4 4 - 0 . 3 2 - 0 . 2 6 - 0 . 1 7 - 0 . 1 0 0 . 8 5 0 . 6 2 0 . 4 8 0 . 3 7 0 . 2 2 0 . 1 2 0 . 10 0 . 0 2 0 , 0 0 0 . - ' 3 0 . 0 8 0.1-:^ 0. 11 7 . 7 7 - 1 . 0 0 - 2 . 0 3 - 1 . 7 0 - I . 5 8 - 1 . 4 7 - 1 . 3 0 - 1 . 2 2 - 1 . 1 4 - 1 . 0 2 - 0 . 9 0 - 0 . 3 4 - 0 . 7 3 - 0 . 7 0 - 0 . 5 9 -'•-.45 - 0 . 3 2 - 0 . 2 4 - 0 . 1 6 - O . 0 3 0 . 9 6 0 . 7 6 0 . 6 0

- . 4 9

0 . 3 2 0 . 2 0 0 . I 6 0 . 1 0 0 . 0 3 ^ . 0 7 0 . 1 : -0 . 1 1 0. 11 9 . 3 2 - 1 . 7 8 - 2 . 3 5 - 1 . 9 5 - I . 7 6 - 1 . 6 3 - 1 . 3 8 - 1 . 2 0 - 1 . 10 - 1 . 0 3 - 0 . 9 2 - 0 . 8 4 - 0 . 7 7 - 0 . 6 3 - 0 . 5 5 - O . / j ? - 0 . 2 8 - 0 . 20 - 0 . 10 - 0 . 0 5 1. "'0 - . 8 3 C.69 r . 5 7 0 . 4 1 0. 29 0 . 2 3 0 . 16 0. 10 " . 12 0. 12 0 . 1 2 0. 12 1 1 . 0 5 - 2 . 7 8 - 2 . 7 2 - 2 . 5 7 - 2 . 0 0 - 1 . 6 0 - 1 . 4 5 - 1 . 3 4 - 1 . 2 0 - 1 . 0 9 - 0 . 9 7 - 0 . 8 7 - 0 . 7 8 - 0 . 6 7 - 0 . 5 1 - 0 . 3 8 - 0 . 2 4 - 0 . 1 6 - 0 . 0 9 - " . 0 5 1.05 " . 9 3 C . 80 '-^.69 0 . 5 0 0 . 36 0 . 3 1 0 . 2 2 0 . 1 4 0 . 1 4 0 . 1 3 ^ \ 1 1 0 . 10 [ 1 2 . 7 8 - 3 . 7 0 - 3 . 2 0 - 3 . 0 0 - 1 . 9 0 - 1 . 7 5 - 1 . 5 0 - 1 . 3 5 - 1 . 2 0 - 1 . 0 5 - 0 , 9 0 - 0 . 7 5 - 0 . 6 0 - 0 . 4 5 - 0 . 2 5 - 0 . 20 - 0 . 19 -f~. 20 - 0 . 20 - - . 20 1 . - 7 1. ---^ " . 8 7 0 . 7 6 0 . 5 7 0 . 4 3 0 . 3 6 0 . 2 7 0 . 1 8 - . 1 7 0 . 1 4 0 . 11 0 . 0 7

Table I I I ( i )

' • ^ - - 0 x / c ^~-,._ L e a d i n g e d g e 1 0 . 0 2 5 0 . 0 5 0 0 . ^ 7 5 0 . 1 0 0 . 1 5 m 0 . 2 0

SI0.25

,2!o.30

§ 1 0 . 3 5 CQ10.40 r i i O . 4 5

g^o.50

g o . 5 5

^ • 0 . 6 0 1 0 . 6 5 10. 70 0 . 7 5 0 . 8 0 — 1 0 . 0 2 5 0 . 0 5 0 0 . 0 7 5 g o . 1 0 ^ ; o . i 5 SH;O.2O CQjO. 2 5 j o . 3 0 ^ J O . 4 0 0 \—1 0 . 5 0 0 . 6 0 0 . 7 0 0 . 8 0 - 2 . 1 0 0 . 8 0 0 . 3 1 0 . 0 3 - 0 . 1 2 - 0 . 2 2 - 0 . 3 2 - O . i i O - 0 . 3 9 - 0 . 7 4 - 0 . 3 7 - 0 . 4 4 - 0 . 4 7 - 0 . 4 6 - 0 . 3 8 - 0 . 3 1 - 0 . 2 3 - 0 . 1 7 - 0 . 1 0 - 0 . 0 6 - 0 . 3 7 ^ - 0 . 4 3 - 0 . 4 7 - 0 . 4 3 - 0 . 4 7 - 0 . 4 2 - 0 . 3 6 - 0 . 6 0 - 0 . 2 8 - 0 . 1 8 - 0 . 10 - 0 . 0 4 0 . 0 2 - 0 . 6 9 0 . 9 8 ' " Ö . " b 6 " ' - 0 , 18 -Q.iO - 0 , 3 8 - 0 , 4 6 - 0 . 5 2 - 0 . 4 9 - 0 . 8 3 - 0 - 4 4 - 0 . 4 9 - 0 . 5 3 - 0 . 4 9 - 0 . 4 2 - 0 . 3 4 - 0 . 2 4 - 0 . 1 9 - 0 . 1 2 - 0 . 0 7 - 0 . 0 9 - 0 , 22 - 0 . 2 7 - 0 . 3 2 - 0 . 3 5 - 0 . 3 3 - O . 2 7 - 0 . 5 4 - 0 . 2 4 - 0 . 1 5 - 0 . 0 8 - 0 . 0 4 0 . 0 3 T r a n s i t 0 . 5 8 1 . 0 2 - 5 . 2 2 ' - 0 . 3 9 - 0 . 4 9 - 0 . 5 3 - 0 . 5 8 - 0 . 6 2 - 0 . 5 8 - 0 . 3 9 - 0 . 5 1 - 0 . 5 4 - 0 . 5 5 - 0 . 5 2 - 0 . 4 4 - 0 . 56 - 0 . 2 6 - 0 . 19 - 0 . 1 3 - 0 . 0 7 0 . 16 - 0 . 0 2 - 0 . 10 - 0 . 17 - 0 . 2 2 - 0 . 2 2 - 0 . 1 8 - O . 4 6 - 0 . 1 9 - 0 . 1 2 - 0 - 0 5 - 0 . v 0 2 0 . 0 3 2 . 0 7 0 . 9 6 - 0 . 5 1 - 0 . 6 2 - 0 . 6 8 - 0 . 6 9 - 0 . 7 0 - 0 . 7 2 - 0 . 6 7 - 0 . 9 7 - 0 . 6 1 - 0 . 5 9 - 0 . 6 0 - 0 . 5 7 - 0 . 4 8 - 0 . 3 7 - 0 . 2 7 - 0 . 2 1 - 0 . 1 3 - 0 . 0 8 ^ . 3 7 0 . 1 6 C . 0 7 - 0 . 0 2 - 0 . 10 - 0 . 1 3 - 0 . 0 9 - 0 . 3 8 - 0 , 1 5 - 0 . 0 7 - 0 - 0 3 0 . 0 1 0 . 0 4 i o n W i r e s a t 27-^^ C h o r d 3 . 4 7 0 . 7 7 7 o 7 8 2 - 0 . 8 6 - 0 , 8 9 - 0 , 8 9 - 0 , 8 5 - 0 . 8 4 - 0 , 7 7 - 1 , 0 3 - 0 . 7 7 - 0 . 6 3 - 0 . 6 4 - 0 . 5 9 - 0 . 4 9 - 0 , 3 9 - 0 . 2 8 - 0 . 2 2 - 0 . 1 4 - 0 . 0 8 0 . 5 7 ^ 0 . 3 3 0 . 2 1 0 . 12 0 . 0 2 - 0 . 0 3 - 0 . 0 2 - 0 . 3 2 - 0 . 0 8 - O . O 3 o - o i 0 . 0 2 0 . 0 6 4 . 9 0 0 , 3 7 • - i 7 2 i - 1 . 1 1 - 1 . 1 0 - 1 . 0 6 - 0 , 9 3 - 0 . 9 4 - 0 , 8 5 - 1 , 1 0 - 0 . 7 7 - 0 . 6 8 - 0 . 6 8 - 0 . 6 4 - 0 . 5 3 - 0 . 4 1 - 0 . 2 9 - 0 . 2 3 - 0 . 1 4 - 0 . 0 8 0 . 7 3 0 . 4 8 0 . 3 4 0 . 2 2 0 . 10 6 . 2 5 - 0 . 18 " - • i : 5 7 " - 1 . 3 7 - 1 . 3 0 - 1 . 2 5 - 1 . 12 - 1 . 0 5 - 0 . 9 8 - 1 . 2 6 - 0 . 7 7 - 0 , 7 7 - 0 . 7 2 - 0 . 6 3 - 0 . 5 6 - 0 . 4 3 - 0 . 3 2 - 0 . 2 4 - 0 . 1 4 - 0 . 0 9 0 . 3 5 0 . 6 3 0 . 4 s 0 . 3 7 0 . 2 2 0 . 0 3 ! 0 . 1 3 0 . 0 6 - 0 . 2 4 - O . O 4 0 . 0 0 0 . 0 2 0 . 0 5 0 , 0 8 0 . 1 3 - 0 , 16 0 . 0 0 0 . 0 3 0 - 0 7 0 . 0 8 0 . 0 9 7 . 7 6 - 0 . 9 1 - 1 . 9 8 - 1 . 6 6 - 1 . 5 4 - 1 . 4 5 - 1 . 2 3 - 1 . 18 - 1 . 0 8 - 1 . 0 1 - 0 . 8 7 - 0 . 3 3 - 0 . 7 8 - 0 . 6 9 - 0 , 5 8 - 0 . 4 4 - 0 . 3 2 - 0 . 2 4 - 0 . 1 5 - 0 . 0 9 0 . 9 3 0 . 7 5 0 . 5 9 0 . 4 7 0 . 3 1 0 . 2 1 0 . 2 0 - 0 . 0 8 0 . 0 6 0 . 0 9 0 . 10 0 . 10 0 . 10 9 . 3 3 - 1 . 7 7 - 2 . 3 7 - 1 . 9 2 - 1 . 7 8 - 1 . 6 2 - 1 . 3 3 - 1 . 18 - 1 . 0 4 - 1 . 1 0 - 0 - 9 2 - 0 . 8 6 - 0 . 7 8 - 0 . 6 8 - 0 . 5 6 - 0 . 4 3 - 0 . 2 8 - 0 . 2 1 - 0 . 1 3 - 0 . 0 8 0 . 9 8 0 . 8 3 0 . 6 8 0 . 5 7 0 . 4 0 0 . 2 9 0 . 2 8 0 . 0 0 0 . 12 0 . 12 0 . 1 3 0 . 11 0 . 10 1 1 . 2 4 - 2 . 6 2 - 2 . 5 8 - 2 . 4 3 - 2 . 0 2 - 1 . 5 2 - 1 . 3 3 - 1 . 2 7 - 1 . 0 9 - 1 . 0 9 - 0 . 9 1 - 0 . 8 2 - 0 . 7 1 - 0 . 5 3 - 0 . 4 2 - 0 . 3 1 - 0 . 2 1 - 0 . 16 - 0 . 1 3 - 0 . 12 1 . 0 2 0 . 9 1 0 . 7 7 0 . 6 3 0 . 4 8 0 . 3 5 0 . 3 3 0 . 0 3 0 . 1 3 0 . 12 0 . 11 0 . 0 9 0 . 0 8 T a b l e I I I ( i i ) 1 3 . 1 4 - 3 - 4 0 - 2 . 9 5 - 2 . 9 2 - 1 . 7 7 - I . 5 8 - 1 . 3 8 - 1 . 2 2 - 1 . 0 2 - 0 . 9 5 - 0 . 7 7 - 0 . 6 2 - 0 . 4 5 - 0 . 3 1 - 0 . 2 4 - 0 . 2 Z i - 0 . 2 3 - 0 . 2 5 - 0 . 2 6 - 0 . 2 7 1 . 0 3 0 . 9 6 0 . 8 2 0 . 7 3 0 . 5 3 0 . 4 0 0 . 3 8 0 . 0 9 0 . 16 0 . 1 5 0 . 1 3 0 . 0 9 0 . 0 4

R = 3 X Transition Wires 10^ at 8/^ Chord L e a d i n g e d g e CD o Co CO CD P ' PM CD O CO <U 0 CQ in CD & O 0 . 0 2 5 0 . 0 5 0 0 . 0 7 5 0. 10 0 . 15 0 . 2 0 0 . 25 0 . 3 0 0 . 3 5 0 . 4 0 0 . 4 5 0 . 5 0 0 . 5 5 0 . 6 0 0 . 6 5 0 . 7 0 0 . 7 5 0 . 8 0 0 . 0 2 5 0 . 0 5 0 0 . 0 7 5 0. 10 0 . 1 5 0 . 2 0 0 . 2 5 0 . 3 0 0 . 4 0 0 . 5 0 0 . 6 0 0 . 7 0 0 . 8 0 - 2 . 0 4 C.79 0 . 3 0 0 . 0 2 - 0 . 0 3 - 0 . 4 2 - 0 . 2 8 - 0 . 4 0 - 0 . 4 5 - 0 . 4 8 - 0 . 4 9 - 0 . 4 9 - 0 . 4 8 - 0 . 4 7 - 0 . 4 0 - 0 . 3 2 - 0 . 2 2 - 0 . 1 7 - 0 . 10 - 0 . 0 7 - 0 . 3 8 -O./44 - 0 . 4 0 - 0 . 6 9 - 0 . 4 5 - 0 , 4 4 - 0 , 4 0 - 0 . 4 1 - 0 . 3 3 - 0 . 1 9 - 0 . 10 - 0 . 0 5 0 . 0 0 0 . 7 2 1.01 - 0 . 1 9 - 0 . 3 6 - 0 . 4 2 - 0 . 7 7 - 0 . 5 2 - 0 . 6 0 - 0 . 6 1 - 0 . 6 2 - 0 . 6 0 - 0 . 5 8 - 0 . 5 7 - 0 . 5 3 - 0 . 4 4 - 0 . 3 5 - 0 . 2 4 - 0 . 18 - 0 . 11 - 0 . 0 7 0 . 1 7 0 . 0 0 - 0 . 0 6 - 0 . 3 5 - 0 . 2 0 - 0 . 2 3 - 0 . 2 3 - 0 . 2 7 - 0 . 2 2 - 0 . 12 - 0 . 0 5 0 . 0 0 0 . 0 3 3 . 6 1 0 . 7 5 - 0 . 8 2 ~ 1 - 0 . 8 2 - 0 . 8 0 - 1 . 1 2 - 0 . 7 6 - 0 . 8 2 - 0 . 7 9 - 0 . 7 8 - 0 . 7 3 - 0 . 6 9 - 0 . 6 6 - 0 . 6 0 - 0 . 5 0 - 0 . 3 9 - 0 . 2 8 - 0 . 2 2 - 0 . 1 5 - 0 . 0 8 0 . 5 5 0 . 3 3 0 . 2 2 - 0 . 0 6 0 . 0 0 - 0 . 0 7 - 0 . 0 8 - 0 , 1 3 - 0 , 12 - 0 . 0 6 - 0 . 0 1 0 . 0 1 0 . 0 3 6 . 6 1 - 0 . 1 3 - 1 . 5 0 - 1 . 3 0 - 1 . 19 - 1 . 3 8 - 0 . 9 9 - 0 . 9 8 - 0 . 9 3 - 0 . 8 8 - 0 . 8 2 0 . 7 ^ -- 0 . 7 0 - 0 . 6 2 - 0 . 5 1 - 0 . 4 0 - 0 . 2 8 - 0 . 2 0 - 0 . 1 4 - 0 . 0 8 0 . 8 3 0. 61 0 . 4 9 0 . 2 4 0 . 2 2 0 . 12 0 . 10 0 . 0 0 - 0 . 0 2 0 . 0 2 0 . 0 6 0 . 0 7 0 . 0 8 9 . 5 0 - 1 , 6 5 - 2 . 3 6 - 1 . 8 6 - 1 . 6 9 - 1 . 7 8 - 1 . 19 - 1 . 18 - 1 . 0 9 - 1 . 0 0 - 0 . 9 0 - 0 . 8 3 - 0 . 7 6 - 0 . 6 8 - 0 . 5 3 - 0 . 4 0 - 0 . 2 8 - 0 . 2 0 - 0 . 1 4 - 0 . 0 8 0 . 9 8 0 . 8 1 0 . 6 8 0 . 5 0 0 . 4 7 0 . 2 5 0 . 2 2 0 . 1 3 0 . 0 7 0 . 10 0. 10 0. 10 0. 10 1 1 . 1 3 - 2 . 6 0 - 2 . 6 5 - 2 . 4 0 - 1 . 8 5 - 1 . 6 4 - 1 . 4 0 - 1 . 2 8 - 1 . 17 - 1 . 0 6 - 0 . 9 4 - 0 . 8 7 - 0 . 7 7 - 0 . 6 6 - 0 . 5 0 - 0 . 3 8 - 0 . 2 6 - 0 . 1 8 - 0 . 1 2 - 0 . 0 9 1.00 0 . 9 0 0 . 7 7 0 . 6 1 0 . 4 5 0 . 3 2 0 . 2 8 0 . 2 0 0 . 12 0, 12 0 . 12 0 . 11 0, 10

T r a n s i t i o n W i r e s a t 4/^ Chord ^~-~^ o x/c^-~5i-.^ L e a d i n g e d g e CD o Co n CO u CD Pi P: & CD O ui CQ ?H CD & O PI

0,025

0.050

0,075

0.10

0.15

0. 20

0.25

0.30

0.35

0,40

0,45

0.50

0.55

0.60

0.65

0.70

0.75

0.80

0.025

0.050

0.075

0.10

0.15

0,20

0.25

0.30

0,40

p. 50

0.60

0.70

0.80

-2.18

0.80

0.33

-0.21

-0.07

-0.20

-0.30

-0.41

-0.46

-0.49

-0.49

-0.49

- 0 . 4 8

- 0 . 4 4

-0.39

- 0 . 3 7

- 0 . 3 5

-0.19

-0.05

- 0 . 0 3

-0.32

-Q.70

- 0 . 4 8

-0.40

- 0 . 4 5

-0.42

- 0 . 39

-0.39

-Ü.3I

- c . 17

-0.10

- 0 . 0 3

0.02

—

0.72

1.03

- 0 . 18

-0.69

- 0 . 3 9

- 0 . 5 0

- 0 . 5 7

- 0 . 6 2

- 0 . 6 3

- 0 . 6 5

- 0 . 6 2

-0.60

- 0 . 5 8

- 0 . 5 5

-0.49

- 0 . 3 8

- 0 . 2 6

- 0 . 19

- 0 . 1 3

- 0 . 0 7

0. 18

- 0 . 2 8

- 0 . 0 8

- 0 . 1 8

- 0 . 2 5

- 0 . 2 6

- 0 . 2 5

- 0 . 2 7

- 0 . 2 4

- 0 . 1 5

- 0 . 0 8

0

0.03

3.63

0.77

- 0 . 7 7

- 1 . 1 8

-0.76

-0,78

-0.80

- 0 . 8 3

-0.80

-0,77

- 0 , 7 3

- 0 . 6 8

-0.65

-0.59

-0.49

-0.38

-0.27

-0.20

- 0 , 1 3

-0.07

0.58

0.13

0.23

0.12

0

-0,06

-0.08

-0, 10

- 0 . 10

- 0 . 0 4

0

0.02

0.05

6.58

- 0 . 10

- 1 . 4 3

- 1 . 6 5

- 1 . 2 7

- 1 . 0 6

- 1 . 0 2

- 1 . 0 0

- 0 . 9 4

- 0 . 8 8

- 0 . 8 2

- 0 . 7 6

-0.70

- 0 . 6 4

-0.52

-0.40

- 0 . 2 8

- 0 . 2 0

- 0 . 1 3

- 0 . 0 7

0.33

0.48

0.48

0.36

0.20

0. 10

0.07

0.01

- 0 . 0 2

0.02

0.05

0.07

0.09

9.62

- 1 . 6 3

-2.16

-2.22

- 1 . 6 7

-1.36

-1.29

-1.20

-1.10

-1.00

-0.90

- 0 . 8 3

-0.75

- 0 . 6 4

-0.50

- 0 . 3 7

- 0 . 2 5

- 0 . 1 7

-0.11

-0.08

1.00

0.84

0.69

0.55

0.39

0.27

0.22

0.13

0.08

0.10

0. 10

0. 10

0. 10

11.37

- 2 , 5 0

- 2 . 5 5

- 2 . 4 5

-1,70

-1.48

-1.38

- 1 . 2 7

- 1 . 12

-1.02

-0.88

-0.78

-0.68

- 0 . 5 5

-0.40

-0.28

-0.19

- 0 . 18

- 0 . 1 7

- 0 . 16

1.00

0.90

0.73

0.62

0.45

0.33

0,28

0,20

0, 12

0. 12

0. 10

0.07

0.05

Table I I I (iv)

R = 3 X 10^

Transition Wires at ^7 Chord

f---^^ 0 Leading edge CD Ü CO m P H CD p. P i t) f LoY/e r Surfac e 0.025 0.050 0.075 0. 10 0. 15 0.20 0.25 0.30 0.35 0.40 0.45 0,50 0 , 5 5 0.60 0.65 0,70 0,75 0.80 0,025 0.050 0.075 0. 10 0.15 0,20 0,25 0.30 0.40 0.50 0.60 0.70 0.80 -2.21 0.82 0,30 0.02 - 0 . 1 3 - 0 . 2 3 -0.32 -0.42 - 0 . 4 7 - 0 . 4 8 -0.49 -0.49 -0.49 -0.45 -0.39 - 0 . 3 8 - 0 . 3 5 -0.20 -0.05 - 0 . 0 3 -0.60 - 0 . 3 5 - 0 . 4 2 - 0 . 4 4 - 0 . 4 6 - 0 . 4 3 - 0 . 3 9 -0.39 - 0 . 3 1 - 0 . 18 - 0 . 10 - 0 . 0 3 0.02 0.59 1.00 - 0 . 18 - 0 . 3 8 - 0 . 4 8 - 0 . 5 3 - 0 . 5 8 - 0 . 6 3 - 0 . 6 4 - 0 . 6 5 -0.62 -0.59 - 0 . 5 7 - 0 . 5 3 - 0 . 4 8 - 0 . 4 7 -0.40 - 0 . 12 - 0 . 0 8 - 0 . 0 5 0.22 0.00 -0.08 - 0 . 16 -0.22 -0.22 -0.22 -0.25 - 0 . 21 - 0 . 1 3 - 0 . 0 7 0.00 0.06 3.57 0.80 - 0 . 9 8 - 0 . 7 7 - 0 . 8 3 - 0 . 8 4 -0.82 - 0 . 8 3 -0.80 -0.78 - 0 . 7 4 -0.69 - 0 . 6 7 -0.60 -0.51 -0.40 - 0 . 2 8 -0.21 - 0 . 1 4 - 0 . 0 8 0.58 0.33 0.22 0 . 1 3 0.00 - 0 . 0 7 - 0 . 0 8 - 0 . 11 - 0 . 11 - 0 . 0 5 0.00 0.03 0.07 6.80 - 0 . 0 5 -1.87 - 1 . 0 8 - 1 . 16 - 1 . 10 - 1 . 0 3 -0.99 - 0 . 9 3 -0.87 -0.80 - 0 . 7 4 -0.68 -0.61 -0.50 -0.38 -0.27 -0.20 - 0 . 1 4 -0.07 0.81 0.60 0,45 0.35 0.20 0. 10 0.07 0.01 -0.02 0.02 0.05 0.07 0.08 9.65 -1.50 - 2 . 8 7 - 1 . 5 2 -1,57 - 1 . 4 5 -1.30 -1.20 - 1 . 10 -1.01 -0.90 -0.82 - 0 . 7 3 -0.60 - 0 . 4 7 - 0 . 3 6 - 0 . 2 4 - 0 . 1 7 - 0 . 1 3 - 0 . 11 0.99 0.82 0.67 0.54 0.38 0.26 0.22 0.13 0.07 0,09 0, 10 0,08 0.07 11.49 - 2 . 4 4 - 3 . 2 4 - I . 7 I -1.69 -1.55 -1.35 - I . 2 3 -1.10 -0.97 -0.83 -0.71 -0.56 -0.41 -0.28 - 0 . 2 4 -0.22 - 0 . 2 3 -0.23 - 0 . 2 3 1.02 0.87 0.73 0.62 0.55 0.32 0.27 0. 18 0. 11 0. 11 0.09 0.07 0.04

Transition Fre e <-:r o • x / c ^^^^ L e a d i n g eds-e Uppe r Surfac e 1 CD o Cd CQ ft o 0 . 0 2 5 0 . 0 5 0 . 0 7 5 0 , 10 0 . 1 5 0 , 2 0 0 , 2 5 0 . 3 0 0 . 3 5 0 . 4 0 0 . 4 5 0 . 5 0 0 . 5 5 0 . 6 o 0 . 6 5 0 . 7 0 0 - 7 5 0 . 8 0 0 . 0 2 5 0 . 0 5 0 . 0 7 5 0 . 10 0 . 1 5 0 . 2 0 0 . 2 5 0 . 3 0 0 . 4 0 0 . 5 0 0 . 6 0 0 . 7 0 0 . 8 0 - 2 . 0 4 0 . 8 0 0 . 3 2 0 . 0 5 - 0 . 10 - 0 . 1 9 - 0 . 3 0 - 0 . 4 0 - 0 . 4 4 - 0 . 4 6 - 0 . 4 7 - 0 . 4 7 - 0 . 4 7 - 0 - 4 5 - 0 . 3 9 - 0 . 3 6 - 0 . 1 5 - 0 . 1 2 - 0 . 0 5 0 . 0 0 - 0 . 3 8 - 0 . 4 4 - 0 . 4 5 - 0 . 4 7 - 0 . 4 7 - 0 . 4 3 - 0 . 4 0 - 0 . 3 9 - 0 . 3 4 - 0 . 1 7 - 0 . 0 8 - 0 . 0 4 0 . 0 3 - 0 . 55 1.00 0 . 0 7 - 0 . 1 7 - 0 . 2 9 - 0 . 3 6 - 0 . kh - 0 . 5 1 - 0 . 5 4 - 0 . 5 5 - 0 . 5 5 - 0 . 5 3 - 0 . 5 3 - 0 . 5 0 - 0 . 4 4 - 0 . 3 9 - 0 . 18 - 0 . 1 4 - 0 . 3 7 - 0 . 01 - 0 . 0 8 - 0 . 2 1 - 0 . 2 6 - 0 . 31 - 0 . 3 5 - 0 . 3 4 - 0 . 31 - 0 . 3 2 - 0 . 2 8 - 0 . 1 7 - 0 . 0 6 - 0 . 0 2 0 . 0 3 0 . 6 9 1.00 - 0 . 2 1 - 0 . 3 9 - 0 . 4 8 - 0 . 5 3 - 0 . 5 8 - 0 . 6 3 - 0 . 6 4 - 0 . 6 3 - 0 . 6 2 - 0 . 6 0 - 0 . 5 9 -^'55 - 3 . 5 0 - D . 3 6 - 3 . 2 1 - 3 . 1 7 - 0 . 0 8 - 0 . 0 3 0 . 1 7 - 0 . 0 1 - 0 . 0 9 - 0 . 1 6 - 0 . 2 3 - 0 . 2 4 - 0 . 2 3 - 0 . 2 5 - 0 . 2 3 - 0 . 1 4 - 0 . 0 3 0 . 0 0 0 . 0 5 2 . 0 4 0 . 9 8 - 0 . 5 2 - 0 . 6 2 - 0 . 6 9 - 0 . 7 1 - 0 . 7 2 - 0 . 7 5 - 0 . 7 4 - 0 . 7 2 - 0 . 7 0 - 0 . 6 7 - 0 . 6 4 - 0 . 6 1 - 0 , 5 5 - 0 . 3 3 - 0 . 2 4 - 0 . 1 9 - 0 . 10 - 0 . 0 3 0 . 3 9 0. 18 0 . 0 7 - 0 . 0 1 - 0 . 11 - 0 . 1 5 - 0 . 1 5 - 0 . 1 7 - 0 . 1 7 - 0 . 0 3 0 . 0 1 0 . 0 2 0 . 0 6 1 3 . 4 9 0 . 7 5 - 0 . 8 6 - 0 . 8 7 - 0 . 8 9 - 0 . 8 8 - 0 . 8 6 - 0 . 8 6 - 0 . 8 3 - 0 . 7 9 - 0 . 7 6 - 0 . 7 2 - 0 . 7 0 - 0 . 6 5 - 0 . 5 1 - 0 . 3 5 - 0 . 2 7 - 0 . 21 - 0 . 11 - 0 . 0 5 0 - 5 8 0 . 3 5 0 . 2 3 0 . 12 0 . 0 1 - 0 . 0 6 - 0 . 0 7 - 0 . 10 - 0 . 12 - 0 , 0 5 0 , 0 1 0 . 0 4 0 , 0 7 4 . 8 8 0 . 3 4 - 1 , 2 3 - 1 . 1 3 - 1 . 1 2 - 1 . 0 7 - 1 . 0 0 - 0 . 9 7 - 0 , 9 3 - 0 . 8 8 0 . 8 3 -- 0 , 7 5 - 0 , 6 8 - 0 . 6 3 - 0 . 5 2 - 0 , 3 9 - 0 . 2 9 - 0 . 2 1 - 0 . 12 - 0 . 0 5 0 . 7 3 0 . 5 0 0 . 3 6 0 . 2 5 0 - 1 1 0 . 0 3 0 - 0 1 - 0 . 0 3 - 0 . 0 6 - 0 . 0 1 0 . 0 3 0 . 0 5 0 . 0 8 6 . 4 6 0 - 2 4 - 1 . 6 0 - 1 . 4 0 - 1 . 3 4 - 1 . 2 6 - 1 . 1 5 - 1 . 0 7 - 0 . 9 9 - 0 . 9 1 - 0 - 8 4 - 0 . 7 8 - 0 . 7 3 - 0 . 6 6 -0-5^1. - 0 . 4 1 - 0 . 3 0 - 0 . 22 - 0 . 1 3 - 0 . 0 5 0 . 8 6 0 . 6 3 0 . 4 9 0 . 3 7 0 . 2 2 0 . 1 3 0 - 0 9 0 . 0 4 - 0 . 0 1 0 . 0 4 0 . 0 6 0 . 0 7 0 . 0 9 7 . 8 5 - 0 . 9 s - 2 . 0 1 - 1 . 6 8 - 1 . 5 7 - i . / 4 i ; - 1 . 2 1 - 1 . 1 4 - 1 . 0 6 - 0 . 9 8 - 0 . 8 9 - 0 . 8 3 - 0 . 7 7 - 0 . 6 9 - 0 . 5 6 - 0 . 4 3 - 0 . 3 1 - 0 . 2 2 - 0 . 1 3 - 0 . 0 5 0 . 9 5 0 . 7 4 0 . 6 0 0 . 4 8 0 . 3 2 0 . 2 1 0 . 1 7 0 . 11 0 . 0 5 0 . 0 8 0 . 0 9 0 . 10 0 . 10 9 . 3 5 - 1 . 9 1 - 2 . 4 5 - 2 . 0 2 - 1 . 7 5 - 1 , 4 5 - 1 . 3 4 - 1 , 2 6 - 1 . 16 - 1 . 0 5 - 0 . 9 5 - 0 , 8 7 - 0 . 7 9 - 0 . 7 0 - 0 . 5 6 - 0 . 4 2 - 0 . 3 0 - 0 . 2 0 - 0 . 11 - 0 , 0 4 1.01 0 . 8 4 0 . 7 0 0 . 5 3 0 . 4 1 0 . 2 8 0 . 2 3 0 . 1 7 0 . 0 9 0.'11 0 . 11 0 . 11 0 . 10 1 1 . 1 5 - 2 . 8 8 - 2 . 8 8 - 2 . 0 8 - 1 . 8 8 - 1 . 6 5 - 1 . 4 6 - 1 . 3 4 - 1 . 2 1 - 1 . 0 8 - 0 . 9 7 - 0 . 8 6 - 0 . 7 7 - 0 . 6 5 - 0 . 4 9 - 0 . 3 4 - 0 . 2 1 - 0 . 1 3 - 0 . 0 9 - 0 . 0 6 1. 0 4 0 . 9 1 0 . 7 9 0 . 6 6 0 . 4 9 0 . 3 5 O.30 0 . 2 3 0 . 1 4 0 . 1 4 0 . 1 3 0 . 1-1 0 . 0 9 1 2 . 7 3 - 3 . 8 8 - 3 . 3 2 - 2 . 2 4 - 2 . 0 2 - 1 . 7 4 - 1 . 5 0 - 1 . 3 4 - 1 . 1 8 - 1 . 0 2 - 0 . 8 8 - 0 . 7 6 - 0 . 6 3 - 0 . 4 8 - 0 . 3 3 - 0 . 3 0 - 0 . 2 7 - 0 . 2 7 - 0 . 2 5 - 0 . 2 4 I.Oit 0 . 9 6 0 . 8 5 0 . 7 3 0 . 5 5 0 . 4 1 0 . 3 5 0 . 2 7 0 . 1 7 0 . 1 5 0 . 1 4 0 . 10 0 . 0 7 Table IV (±)

:?RESSURE COE^^FICIENT DISTRIBUTIONS R ^ 3 X 10^ T r a n s i t i o n W i r e s a t 27-^^^ C h o r d . ^ / ^ ' ^ - ^ L e a d i n g e d g e CD Ü Cd l p u CQ u CD P' CD O Cd <Pi u CQ ft % O 0 , 0 2 5 0 , 0 5 0 0 . 0 7 5 0, 10 0 . 15 0 . 2 0 0 . 2 5 0 . 3 0 0 . 3 5 0 . 4 0 0 . 4 5 0 . 5 0 0 . 5 5 0 . 6 0 • 0 . 6 5 0 . 7 0 0 . 7 5 0 . 8 0 0 . 0 2 5 0 , 0 5 0 0 , 0 7 5 0 . 10 0 . 1 5 0 . 2 0 0 . 2 5 0 . 3 0 0 . 4 0 0 . 5 0 0 . 6 0 0 . 7 0 0 . 8 0 - 2 . 0.1' 0 . 7 9 0 . 3 3 0 . 0 5 - 0 . 10 - 0 . 1 9 - 0 . 30 - 0 . 3 8 - 0 . 38 - 0 . 70 -Q. 41 - 0 . 4 4 - 0 . 4 4 - 0 . 4 3 - 0 . 36 - 3 . 2 7 - 0 . 1 9 - 0 . 1 4 - 0 . 0 7 - 0 . 0 2 - 0 . 3 8 - 0 . 4 4 - 0 . 4 5 - 0 . 4 7 - 0 . 4 6 - 0 . 4 2 - 0 . 3 4 - 0 . 4 3 - 0 . 3 0 - 0 . 1 9 - 0 . 1 0 - 0 . 0 5 0 . 0 1 - 0 . 5 9 0 . 9 9 0 . 0 7 - 0 . 1 6 - 0 . 2 8 - 0 . 3 5 - 0 . 4 3 - 0 . 5 0 - 0 . 4 8 - 0 . 8 0 - 0 . 4 8 - 0 . 5 0 - 0 . 5 0 - 0 . 4 8 - 0 . 3 9 - 0 . 3 0 - 0 . 2 2 - 0 . 1 6 - 0 . 0 8 - 0 . 0 2 - 0 . 0 9 - 0 . 2 2 - 0 . 2 6 - 0 . 3 1 - 0 . 3 4 - 0 . 3 2 - 0 . 2 6 - 0 . 3 6 - 0 . 2 6 - 0 . 1 5 - 0 . 0 7 - 0 . 0 3 0 . 0 2 0 . 7 6 1.02 - 0 . 2 0 - 0 . 3 8 - 0 . 4 7 - 0 . 5 2 - 0 . 5 6 - 0 . 6 0 - 0 . 5 7 - 0 . 8 9 - 0 . 5 4 - 0 . 5 6 - 0 . 5 5 - 0 . 5 2 - 0 . 4 3 - 0 . 3 2 - 0 . 2 4 - 0 . 1 7 - 0 . 0 9 - 0 . 0 3 0. 17 - 0 . 11 - 0 . 0 9 - 0 . 16 - 0 . 2 2 - 0 . 2 3 - 0 . 1 7 - 0 . 2 9 - 0 . 21 - 0 . 12 - 0 . 0 5 - 0 . 0 1 0 . 0 3 2 . 1 3 ' 0 . 9 8 - 0 . 5 1 - 0 . 6 1 - 0 . 6 8 - 0 . 6 9 - 0 . 71 - 0 . 7 2 - 0 . 6 6 - 0 . 9 8 - 0 . 6 0 - 0 . 6 1 - 0 . 5 9 - 0 . 5 5 - 0 . 4 5 - 0 . 3 5 - 0 . 25 - 0 . 1 9 - 0 . 10 - 0 . 0 4 0 . 3 9 0 . 18 0 . 0 8 - 0 . 0 1 - 0 . 10 - 0 , 1 4 - 0 . 0 9 - 0 . 2 1 - 0 . 16 - 0 . 0 8 - 0 . 0 2 0 . 0 1 0 . 0 5 3 . 5 5 ^ 0 . 7 6 •

-Ö7B4

- 0 . 8 9 - 0 . 8 9 - 0 . 8 7 - 0 . 3 4 - 0 . 8 3 - 0 . 7 7 - 1 . 0 7 - 0 . 7 0 - 0 . 7 0 - 0 . 6 4 - 0 . 5 9 - 0 . 4 9 - 0 . 3 7 - 0 . 2 7 - 0 . 2 0 - 0 . 11 - 0 . 0 4 0 . 5 7 0 . 3 4 0 . 2 2 0 . 12 0 . 0 1 - 0 . 0 4 - 0 . 0 1 - 0 . 1 4 - 0 . 11 - 0 . 0 4 0 . 0 1 0 . 0 3 0 . 0 6

6.37

- 0 . 2 2 ' - 1 . 6 0 - 1 . 3 8 - 1 . 3 3 - 1 . 2 4 - 1 . 13 -1.0^^4 - 0 . 8 9 - 1 . 0 8 - 0 , 8 2 - 0 . 7 7 - 0 , 7 2 - 0 . 6 5 - 0 . 5 3 - 0 . 4 0 - 0 . 30 - 0 . 2 1 - 0 . 12 - 0 . 0 5 0 . 8 5 0 . 6 3 0 . 4 9 0 . 3 7 0 . 2 2 0 . 1 3 0 . 1 4 0 . 0 0 0 . 0 0 0. 0 4 0 . 0 6 0 . 0 7 0 . 0 8 9 . 4 2 - 1 - 8 4 - 2 . 4 0 - 2 . 0 0 - 1 . 7 2 - 1 . 4 3 - 1 . 3 1 - 1 . 21 - 1 . 0 4 - 1 . 2 3 - 0 . 9 3 - 0 . 85 - 0 . 7 7 - 0 . 6 8 - 0 . 5 4 - 0 . 4 1 - 0 . 2 9 - 0 . 20 - 0 . 11 - 0 . 0 4 1.00 0 . 8 3 0 . 6 9 0 . 5 7 0 . 4 0 0 . 2 9 0 . 2 8 0 . 1 3 0 . 10 0. 11 0 . 11 0. 10 0 . 10 1 1 . 0 8 - 2 . 7 8 - 2 , 3 1 - 2 . 0 5 - 1 , 8 4 - 1 , 6 1 - 1 . 4 2 - 1 . 2 9 - 1 . 11 - 1 . 2 6 - 0 . 9 5 - 0 . 8 6 - 0 . 7 7 - 0 . 6 5 - 0 . 5 0 - 0 . 3 7 - 0 . 2 5 - 0 . 16 - 0 . 10 - 0 . 0 5 1 . 0 3 0 . 9 0 0 . 7 8 0 . 6 5 0 , 4 8 0 , 3 6 0 . 3 4 0 . 2 0 0 . 1 5 0 . 1 4 0 . 1 3 0. 11 0 . 0 9 T a b l e IV ( ü ^

Transition Wires at 8/^ Chord. Leading edge CD Ü cd iPi U :^ CO u CD p.

ê

CD O cd <w CQ CD O PI ., 0,025 0.050 0.075 0. 10 0. 15 0.20 0.25 0.30 0.35 0.40 0,45 0.50 0.55 0.60 0.65 0.70 0,75 0.Ö0 0,025 0.050 0.075 0.10 0.15 0,20 0,25 0,30 0,40 0,50 0,60 0.70 0,80 -2.08 0.78 ^ 0.33 0.05 -0,06 -0.30 -0.28 - 0 . 3 8 - 0 . 4 3 - 0 . 4 5 -0.45 -0.46 -0.46 - 0 . 4 4 - 0 . 3 6 -0.27 -0.20 - 0 . 1 4 -0.07 -0.02 - 0 . 3 8 - 0 . 4 4 -0.39 - 0 . 8 4 -0.46 -0.46 -0.40 -0,38 -0,32 -0.19 - 0 . 11 -0.05 -0.01 —— . 0.76 1.03 -0.19 -0.35 -0.42 -0.66 - 0 . 5 3 -0.61 -0.62 -0.62 -0.59 - 0 . 5 8 -0.55 -0,52 - 0 . 4 3 -0.32 - 0 , 2 4 - 0 , 18 -0,09 - 0 , 0 3 0.16 -0.01 - 0 . 0 4 -0.47 -0.22 - 0 . 2 7 - 0 , 2 4 - 0 , 2 4 - 0 , 2 3 - 0 . 1 3 -0.05 -0.02 0,02 3,66 0,77 -0,82 -0, 82 -0,81 -1,01 -0,79 -0,82 -0,79 -0.76 -0,71 -0.68 - 0 . 6 4 -0,59 -0,48 -0.36 -0.27 -0.20 - 0 . 11 - 0 . 0 4 0.57 0.34 0.25 - 0 . 1 3 0.00 -0.08 -0.08 - 0 . 10 -0.12 -0.05 -0.01 -0,01 0.04 6.62 - c . 16 - 1 . 56 - 1 , 3 4 -1.26 -1.36 - 1 , 0 3 -1.02 -0.96 -0.89 -0.82 -0,77 -0.71 - 0 . 6 3 -0.51 -0.38 -0.28 -0.19 - 0 , 10 -0.05 0,87 0.61 0.50 0.17 0.25 0,09 0,07 0,03 -0.01 0.02 0.05 0.05 0.06 9.56 - 1 , 7 4 -2,37 - 1 , 9 4 -1,56 -1,71 -1.31 - 1 . 2 2 - 1 . 12 -1.01 -0.92 - 0 . 8 4 - 0 . 7 5 -0.65 -0.51 - 0 . 3 7 - 0 . 2 5 - 0 , 16 - 0 , 10 - 0 . 0 5 1.00 0.82 0.70 0.45 0.39 0.26 0,21 0,15 0.08 0.09 0. 10 0.08 0.08

1

11.28 - 2 . 6 3 -2.69 - 1 . 9 4 -1.68 -1.86 -1.39 -1.27 - 1 . 14 -1.03 -0.90 -0.81 -0.71 -0.59 -0.43 -0.30 -0.20 -0.15 - 0 . 1 3 -0.10 1.01 0.88 0.77 0.55 0.47 0.33 0.28 0.20 0. 11 0. 11 0. 11 0.08 0.07 Table IV (iii)

R ^ 8 X 10^

Transition Wires at kZ Chord

x/c^^-^l -2.00

Leading CD o Co u CO u CD P^ P i i=> CD f) Cd <Pi u •a CQ U CD ^ O 1 ^ 0 . 0 2 5 0 . 0 5 0 0 . 0 7 5 0 . 1 0 0 . 1 5 0 . 2 0 0 . 2 5 0 . 3 0 0 . 3 5 0 . 4 0 0 . 4 5 0.50 0 . 5 5 0.60 0 . 6 5 0.70 0 . 7 5 0 . 8 0 0.025 0.050 0 . 0 7 5 0.10 0 . 1 5 0.20 0 . 2 5 0 . 3 0 0 . 4 0 0.50 0 . 6 0 0.70 0.80 0.79

6,34

- 0 . 26 - 0 , 0 5 - 0 . 1 6 - 0 . 3 2 - 0 . 38 - 0 . 43 - 0 . 4 5 -Ü.45 - 0 . 4 5 -O.Ü.5 - C . 4 4 - 0 . 3 6 - 0 . 2 7 - 0 . 20 - 0 . 1 5 - 0 . 0 7 - 0 . 0 2 - 0 . 3 3 - 0 . 8 8 - 0 . 3 4 - 0 . 4 3 - 0 . 4 6 - 0 . 4 5 -C. 39 - 0 . 3 7 - 0 . 3 1 - 0 . 1 9 - 0 . 1 0 - 0 . 0 5 0.01 0 . 7 3 1.03 - 0 . 1 7 - 0 . 7 9 - 0 . 3 9 - 0 . 47 - 0 . 5 4 - 0 . 6 0 - 0 . 6 2 - 0 . 6 1 - 0 . 5 9 - 0 . 5 7 - 0 . 5 6 - 0 . 5 1 - 0 . 4 3 - 0 . 3 3 - 0 . 2 4 - 0 . 1 7 - 0 . 0 9 - 0 . 0 3 - -- 0 . 3 5 - 0 . 0 1 - 0 . 1 4 - 0 . 2 2 - 0 . 2 6 - 0 . 2 3 -0.2k - 0 . 2 2 - 0 . 1 3 - 0 . 0 5 - 0 . 0 3 0 . 0 3 3.58 0 . 7 7 - 0 . 7 8 - 1 . 3 6 - 0 . 7 6 - 0 . 7 8 - 0 . 8 0 - 0 . 8 2 - 0 . 7 9 - 0 . 7 6 - 0 . 7 1 - 0 . 6 7 - 0 . 6 4 - 0 . 5 8 - 0 . 4 8 - 0 . 3 6 - 0 . 2 6 - 0 . 1 9 - 0 . 1 1 - 0 . 0 4 0.57"" 0. 11 0 . 2 6 0- 12 0 . 0 0 - 0 . 0 7 - 0 , 0 7 - 0 . 10 - 0 . 11 - 0 . 0 5 0 . 0 0 0 . 0 1 0 . 0 4 6.61 - 0 . 1 5 - 1 . 5 2 ' - 2 . 0 0 - 1 . 16 - 1 . 1 3 - 1 . 0 7 - 1 . 0 4 - 0 . 9 8 - 0 . 9 0 - 0 . 8 3 - 0 . 7 8 - 0 . 7 2 - 0 . 6 3 - 0 . 5 1 - 0 . 3 8 - 0 . 2 7 - 0 , 19 - 0 . 1 1 - 0 , 0 4 0.86 0.46 0,49 0-.35 0 . 2 0 0.09 0 . 0 7 0 . 0 2 - 0 . 0 2 0.01 0 . 0 5 0 . 0 5 0 . 0 5 9 . 8 0 - 1 . 7 2 - 2 . 2 3 - 1 . 6 1 - 1 . 6 4 - 1 . 4 5 - 1 . 3 c - 1 . 2 1 - 1 . 10 - 1 - 0 0 - 0 . 9 0 - 0 . 8 1 - 0 . 7 1 - 0 . 6 0 - 0 . 4 5 - 0 . 3 1 - 0 . 2 1 - 0 . 1 4 - 0 . 0 9 - 0 . 0 6 1.00 0 . 8 4 0 . 6 9 0 , 5 5 0-38 0 . 2 6 0.21 0 . 1 5 0 . 0 8 0.09 0 . 0 9 0 . 0 8 0 . 0 6 1 1 . 4 5 - 2 . 5 8 - 2 7 ? 3 - 1 . 9 2 - 1 . 8 0 - 1 . 5 7 - 1 . 3 8 - 1 . 2 5 - 1 . 1 1 - 0 . 9 8 - 0 . 8 5 - 0 . 7 3 - 0 . 6 0 - 0 . 4 5 - 0 . 3 0 - 0 . 2 3 - 0 . 2 0 - 0 . 2 0 - 0 . 19 - 0 . 1 9

ïToT

0.89 0-75 0 . 6 3 0.46 0-33 0 . 2 7 0.20 0. 11 0. 11 0. 10 0 . 0 8 0 . 0 5 Table IV (ivl

Transition Wires at 1/, Chord

^/^--C.

L e a d i n g e d g e CD Ü Cd <Pi CQ t-i CD 1—'-' P I P) CD Ü Cd "P ft CO ft CD O P5 0 . 0 2 5 0 . 0 5 0 0 . 0 7 5 0 . 10 0 . 15 0 . 2 0 0 . 2 5 0 . 3 0 0 . 3 5 0 . 4 0 0 . 4 5 0 . 5 0 0 . 5 5 0 . 6 0 0 . 6 5 0 . 7 0 0 . 7 5 0 . 8 0 0 . 0 2 5 " 0 . 0 5 0 0 . 0 7 5 0 . 10 0 . 1 5 0 . 2 0 0 . 2 5 0 . 3 0 0 . 4 0 0 . 5 0 0 . 6 0 0 . 7 0 0 . 8 0 „.-.?• Pö„. 0 . 8 2 0 . 3 3 0 . 0 4 - 0 . 10 - 0 . 1 9 - 0 . 3 0 - 0 . 4 0 - 0 . 4 3 - 0 . 4 6 - 0 . 4 7 - 0 . 4 6 - 0 . 4 6 -O.LIJ+ - 0 . 3 6 - 0 . 2 7 - 0 . 2 0 - 0 . 1 5 - 0 . 0 7 - 0 . 0 2

-0.T7"

- 0 . 4 0 - 0 . 4 2 - 0 . 4 4 - 0 . 4 5 -O.lih - 0 . 3 9 - 0 . 3 7 - 0 . 3 1 - 0 . 1 8 - 0 . 0 9 - 0 . 0 4 0 . 0 2 0 . 7 7 1 . 0 3 - 0 . 1 4 - 0 . 3 7 - 0 . 4 6 - 0 . 4 8 - 0 . 5 4 - 0 . 6 0 - 0 . 6 2 - 0 . 6 1 - 0 . 5 9 - 0 . 5 7 - 0 . 5 5 - 0 . 5 2 - 0 . 4 3 - 0 . 3 3 - 0 . 2 4 - 0 . 1 7 - 0 . 0 9 - 0 . 0 4 0 7 2 7 " - 0 . 0 1 - 0 . 0 8 - 0 . 16 - 0 . 22 - 0 . 2 6 - 0 . 2 2 - 0 . 2 3 - 0 . 2 1 - 0 . 12 - 0 . 0 5 - 0 . 0 1 0 . 0 3 I - ^

___3-.7L

0 . 7 8 - 0 . 7 0 - 0 . 8 1 - 0 . 8 3 - 0 . 7 9 - 0 . 8 0 - 0 . 8 1 - 0 . 7 8 - 0 . 7 5 - 0 . 7 1 - 0 . 6 7 - 0 . 6 3 - 0 . 5 8 - 0 . 4 7 - 0 . 3 5 - 0 . 2 6 - 0 . 19 - 0 . 10 - 0 . 0 4 0 . 5 6 0 . 3 3 0 . 2 1 0 . 11 - 0 . 0 1 - 0 . 0 1 - 0 . 0 8 - 0 . 11 - 0 . 12 - 0 . 0 5 - O . O 1 . 0 . 0 3 0 . 0 5 6 . 7 4 - 0 . 0 8 - 1 . 3 9 - 1 . 3 1 - I . 2 5 - 1 . 1 4 - 1 . 0 7 - 1 . 0 2 - 0 . 9 6 - 0 . 8 9 - 0 . 8 2 - 0 . 7 6 - 0 . 7 0 - 0 . 6 2 - 0 . 5 0 - 0 . 3 8 - 0 . 2 7 - 0 . 1 3 - 0 . 10 - 0 . 0 4

"o.'84"'"

0 . 6 1 0 . 4 7 0 . 3 5 0 . 2 0 0 , 11 0 . 0 7 0 . 0 2 - 0 . 0 2 0 . 0 1 0 . 0 5 0 . 0 5 0 . 0 5 9 . 8 2 - 1 . 5 5 - 2 . 3 1 - 1 . 7 8 - 1 . 6 4 - 1 . 4 4 - 1 . 2 8 - 1 . 1 8 - 1 . 0 7 - 0 . 9 7 - 0 . 8 6 - 0 . 7 6 - 0 . 6 5 - 0 . 5 3 - 0 . 3 7 - 0 . 2 5 - 0 . 1 7 - 0 . 1 5 - 0 . 1 4 - 0 . 12 0 . 9 9 0 . 8 1 0 . 6 7 0 . 5 5 0 . 3 7 0 . 2 5 0 . 2 1 0 . 1 4 0 . 0 7 0 . 0 8 0 . 0 8 0 . 0 7 0 . 0 7 1 1 . 5 5 - 2 . 3 3 - 2 . 5 5 - 1 . 9 5 - 1 . 7 6 - 1 . 5 2 - 1 . 3 2 - 1 . 1 8 - 1 . 0 3 - 0 . 8 9 - 0 . 7 5 - 0 . 6 2 - 0 . 4 6 - 0 . 3 4 - 0 . 2 6 - 0 . 2 4 - 0 . 2 4 - 0 . 2 5 - 0 . 2 5 - 0 . 2 4

T.~o?

0 . 8 8 0 . 7 5 0 . 6 3 0 . 4 5 0 . 3 2 0 . 2 6 0 , 1 9 0 . 10 0 . 1 0 0 . 0 9 0 . 0 6 0 . 0 3 Table IV (v^

AEROFOIL SECTION NA.CA. 63A2I5 END PLATES PRESSURE - PLOmNG STATION INCIDENCE <<

FIG 2. UFT CHARACTERISTICS.

FIG. I. DIAGRAM OF MCDDEL.

THE EFTICT OF TRANSITION WIRES

o-os O - C O S oos - o o s o-os -o-os TH -•

E EFFECT OF TRANSITION WIRES

.

I

TRANSITION WIRES ON UPPER AND LOWER SURFACES AT:— I - - - 1 % ' c - * ^ 4 < ) -.-.Jhi:

• J

• . c ae 7-5% C -RANSmON FREE O^ 0-4 0-6 O-S lO i-a LIFT COEFFICIENT C^ » OOS O - O O S J S o TRANSITION WRES ON UPPER AND LOWER SURFACES A T : — [ a c 8 % C 27-5% C TRANSITION FREE O O S O C O S 0-2 0-4 0-6 o-e i-o UFT COEFFCIENT C L

-FIG. 4. PITCHING MOMENT CHARACTERISTICS MEASURED AT R <» 8 X lO^

FIG. 3. PITCHWG MOMENT CHARACTERIS-nCS MEASURED

FIG. So. MEASURED UPPER SURFACE PRESSURE DISTRIBUTIONS AT R - 3 X lo'

FIG.5b. MEASURED UPPER SURFACE PRESSURE DISTRIBUTIONS AT R - 3 x l o ' T W EFFECT OF T R A N S i n o N WIRES T « EFFECT OF TRANSfTION W«CS TRANSITION W«ES ON UPPER AND LCWER SURnCE o-a 0 . 4 o - s o - i V{ —

FIG. 5c. MEASURED UPPER SURFACE PRESSURE DISTRIBUTIONS AT R " 3 X 10'

02 04 06 oe io 5 ^

-FG. 5d. MEASURED UPPER SURFACE PRESSURE DISTRIBUTIONS AT R - 3 x 10'

3 O I-O

1

1 \ \ \

N

o / /

V

N

—x -1 UPPER ï

V

\ " - ' • . " ' " — R.3 « URFACE 10» . i 0;4 0 * o.» I.O ( A ^ LOWER SURFACE ' v.'-^ 0 6 0-4 o.a TURBULENT J ^ : * — 1 RE—ATTACHMENT t f LAMINAR \ . , - ^ SEPARATION R - 3 » lO" SEPARATION S \ \ \ \

i

0.2 0.4 0.4 O-fi

F"IG 6. COMPARISON OF PRESSURE DISTRIBUTONS NEAR THE STALL AT TWO \*U.UES OF THE REYNOLDS NUMBER.

FIG. 7 THE APPROXIMATE CHORDWISE POSITONS OF LAMINAR SEPARATION. TURBULENT RE-ATTACHMENT

AND TURBULENT SEPARATION

NO TRANSITON WMES 1 N A . C A 63A2I5 TRANSITION WIRES AT 27.S% CHORD ƒ (PRESENT TESTS)

SMOOTH SURFACE "1 NAC. A. S4A2I2 STANDARD L E ROUCMNEIS ƒ (REFERENCE 4 )

I I I I \

9 2 S4 6-0 6^ 6-4 6.0 LOG,, R —

FIG. ft COMPIMWSON OF LIFT-CURVE SLOPES FOR TEST SECTION