NORWEGIAN SHIP
MODEL EXPERIMENT
TANK THE TECHNICAL UNIVERSITY OF NORWAYA NOTE ON THE THEORY OF
DUCTED PROPELLERS
WORKING IN OPEN WATER
BYKNUT J. MINSAAS
NORWEGIAN
SHIP MODEL EXPERIMENT
TANK PUBLICATION N2 93JANUARY 1967
Contents.
Page
Introduction 1
The Thrust of the Ducted System i
Estimation of Axial and Radial Velocities Induced on Nozzle Profile by the Propeller
L The Thrust of the Nozzle 5
5. Propeller Thrust and Torque 8
6
Comparison between Values Found by
Experiment and Calculation 10
Nozzle Wake and Propeller Thrust 11
Definitions:
Velocities (roeller)
VA Intake velocity of the water into the nozzle system
V1 Total axial velocity in the propeller slip stream
UT Tangential induced velocity in the slip stream
UA Axial induced velocity in the slip stream
UN VUT2
V Velocity of the water at the propeller in the nozzle Velocity at the profile
w Angular velocity of the propeller
(Fig. 3)
V (Fig. 3)
Velocities (nozzle)
Urm The mean of the radial induced velocity on the nozzle by the propeller
0xm The mean of the axial induced velocity on the nozzle
by the propeller
Uam The mean of the axial velocity increase in the slip stream
Constants and Coefficients c
°
K
T
; Thrust
p/2
VA 2 constant of the nozzle systemThrustcoefficient of the nozzle system
pn D
T Kp 2 Thrustcoefficient of the propeller
pn D
KQ Torque coefficient of the propeller
pn
DT
Thrustcoeffjcjent of the nozzle
CL Liftcoefficient of the nozzle profile
V
- Nozzle wake
d1
VAK Masscoefficient or total loss factor
P/D Pitch ratio of the propeller (hydrodynamical) VA
J Advance coefficient of the propeller + nozzle
V
J
-
Velocity coefficient in the slipstream.x nD
E Axial loss factor and drag-lift coefficient
k1 Constant of circulation k2 Radial constant of velocity k3 Axial constant of velocity
Ao/AE Bladearearatio of the propeller
K Goldstein factor
g
l/D Length/Diameter ratio Geometrical dimensions
i Length of the nozzle profile
D Diameter of the propeller
D Diameter of the equivalent vortex ring
r Radius of the propeller
P Pitch of the propeller (hydrodynamical) Rd = Radius of the equivalent vortex ring
X Distance from the leading edge to the point of max. camber
c Chord of the profile
t Max. thickness of the profile
Different definitions
n Number of revolutions of the propeller
T Thrust of the nozzle system (T + Td)
T Thrust of the propeller
Q Torque on the propeller
Total circulation of the nozzle profile
L Lift in general
Z Number of propeller blades
A Area of the equivalent foil
2
A Area of the propeller disk
AE Expanded blade area of the propeller Hydrodynamical angle of pitch
Angle of zero lift
Angle of attack measured from the propelleraxis a - a Effective angle of attack
1 o
a1 Angle between the propeller axis and the chord-line of the nozzle profile.
Summary.
A simple theory for ducted propellers is developed, which makes possible a rough estimation and analysis of different nozzle systems. It takes into consideration the
number of propeller blades and the nozzle shape. The development is based on simple and well-known principles from the vortex
theory. A comparison between experiment and theory shows
good agreement.
Introduction.
The author knows no method of calculation for ducted propellers which gives sufficient agreement with experimental
results. The method of Dickmann and 1eissinger (6) is valid
only for propellers with an infinite number of blades and with no rotation in the slipstream.
The following theory takes into consideration the number of blades and the characteristics of the nozzle profile. The slipstream contraction is not taken into account and it is assumed that the slipstream diameter is equal to the propeller diameter. The diameter of the boss is not considered.
Dxpressions for the thrust of the system, the propeller and
the nozzle are developed.
The Thrust of the Ducted System.
Considering the slipstream some distance from the propeller, the volume streaming through an annular element of
the slipstream will be
which gives
U
VA UT
-
UT UAThis means that
UN /UA + UT2 and the energy is
(U 2 + U 2)
2
Equivalence of the energy in the system gives
dQ w
dTVA +
(U2
+ UT2).
2
By means of the equations for dT, dQ and dm we get
U
2 2
wr.UT=VAUA+(A
T),
2
which gives the thrust
dT 2 r V1 UA dr.
The tangential induced., velocity is UT and the tangential force is
dK = 2 yr V1 UT dr, which gives the torque
dQ 2
p
r2 V1 UT dr.The velocity diagram of the propeller is shown in Fig. 1. It
is seen that
Frg. 2 Fig. i VP
n
n
cor AFig. 8
B I 'A Vrand
V
=V
+00It is assumed that the free vortices being shed from the nozzle
and the propeller are forming regular helicoidal surfaces between
I and II in Fig. 2 with the pitch angle
.The 1nduce. velocity
will then be normal to the surface.
The velocity diagram is
shown in Fig. 3.
Constant V
along the radius is now assumed.
From dT
2ip r V1 UA dr
it follows that
dT
p2iî r(V
+ U)(V
- VA + U)dr
R(V2
- V V
+ (2V
- V )U
+ U
2)r dr.
x A xAx
X 3The equations
o R2iri
2 Urdrw
2 itD2 14and
JX
o (R 2ir Ur dr
KW 2 lTD 24where
X o VwV (P/D---)
give
X nD TI.
K0 2 14pn D
2j
+ (2Jx - J )(P/D_Jx)K+c(P/D_Jx2)).
24 X X O O60
0 L LL L E6.d
9 !.d 80 a 90 7O3) Estimation of Axial and Radial Velocities Induced on Nozzle Profile b the Propeller.
A propeller with an infinite number of blades and
no rotation in the slipstream is considered. It is assumed that the velocity V + U VA + UA is uniformly distributed over the propeller disk. Far ahead of the propeller the pressure is P0. The propeller causes a sudden pressure increase p. Behind the propeller the pressure is Po + Ap. The velocity in the slip-stream just inside the contour of the slip-stream, is VA + UA. Just
outside the contour the velocity is VA. Applying Bernoullis equation for any point on the contour, we get
l/2((VA+UA)2_VA2)
= l/2P(VA+ UA + VA)(VA + - VA)
where
112(VA + + VA) VA +
is the velocity just on the contour and where
VA + UA - VA
is the strength of the vortex sheet replacing the discontinuity
of
the velocity. The equation of the vortex sheet is(VA +
The propeller is now replaced by a semi-infinite vortex cylinder (sheet) inducing a velocity UA uniformly distributed along the
radius. The induced velocities from this cylinder are given by
Küchemann and Weber in "Aerodynamics of Propulsion'.
(8)
A single cylinder can only replace propellers with constant circulation along the radius. If variable circulation0.2 0.4 0.6 0.8 YR 1.0
Fig 9.
dC 120 110 100 go 1.1 tfl. 1.0 0.9 0.8 0.7lo
20 30 40 Fig 12c 50 60Xyc
10 A UA1.0 Jo 0.8 0.6 0.4 0.2 0. E 0.6 0.4 0.2 O 0.8
Jx
1.0 0.2 0.4 0.6Fig. 4
0.8 0.6 1.0 12F,g. 5a
1.6 1.4 I1.1 'Zd 1.0 0.9 0.8 0.7 0.6 0.5 .7
d
t 2 1.4 0.8 0.6 0.4 0.2 O 0.8 1.0 1.2Fig.5b
1.0 1.2 P/D 1.4Fig.5c
0.2 0.4 0.6Fig 30
o 0.8 J0G(x)
2
X
+ (x tg )2 g
Kg is the Goldstein factor.
) The Thrust of the Nozzle.
-5
occurs, the propeller is replaced by an infinite number of coaxial cylinders each having a vortex strength equal to
d y dr.
(Kobylinski: mt. Shipb. Progress No.
88 Vol. 8, 1961). (7)
The estimation of the constants k2 and k3 requires the knowledge of the UA distribution. In Fig. 9 twodistri-butions: one for the usual propeller with elliptical blade area and one for the Kaplan type propeller are given. The distri-butions are based on very rough assumptions. Several vortex cylinders placed inside each other will give the wanted
distribution if the vortex strengths are correctly balanced.
Using the table of Küchemann and Weber
(8)
it will now be possible to estimate the axial and the radial induced velocities on every single point of the nozzle contour. Fig. ! shows the connectionbetween
x and J0 for different valaes of P/ID. K and c are given
in Fig. 5 as functions of P/D x ir
tg ß.
K is given by theequation
K
G(x)xdx,
where
For a foil of chord length i and of infinite length the lift L is given by
L L
12 V2 i
k
VA
where k2 is a constant.
If is the mean of the axial induced velocity from the propeller on the nozzle the circulation will be
-6--We may also write L = pVr, where r is the total circulation. From this
CL V i CL a
i
2 2
where a is the angle of attack.
The same equations are valid for the annular wing but CL is greater because of the self-induced velocities. The ratio CL ran an k -1 CL' a
F1011
is shown in Fig. 6 as a function of lID. If i is the length of the nozzle the thrust will be
where
Td 2rrp R i- U
d d rrn
RL Radius of the equivalent vortex ring
Total nozzle circulation
0rm The mean of the radial Induced velocity on the nozzle from the propeller.
From (V - VA +
U)r
drwe have
Uam
which gives II. where o
+k
2 Dd iCLt
(1 3 VA .Kd=k2 Jo
;i-;
2 VAThe constants k2 and k3 are given later. In Fig. 8 the velocity diagram B is replaced by diagram A. This will have an influence on V only for the highest values of J0. It gives
Kt
0.5 + O.5K.
1)
C1'a
(VA+ U)i
1d
2
where O is given by a constant k3 through
mx
o o
- k
VA
3VA
The induced angle of attack is given by U am o V rm
tga1
k2-Uam mx., VA(l+ V-,
i + k3 VAThe effective angle of attack is
ct a1 - cx0
where a is the angle of zero lift (Fig.
7).
The nozzle isreplaced by a vortex ring with diameter Dd. The nozzle thrust is expressed non dimensional as
Td
Kd
The velocity ratios
i
U1p11U
U i xm I rx and-- dx
VAiJ
VA VAli
VA o o am as functions of give VA O B propeller Ka propeller-8
n dk2
0.303
0.305
k30.2L2
0.260
The drag of the nozzle will reduce the nozzle thrust:
CL sin
-= 1
C1)
Kdj CL sin 0L tg
1
where CL is the liftcoefficient of the profile and 01) the drag-coeffisient. 01) 0.01 gives
d 0.9 - 1.0 for P11) 1.0 - l.1 and J0 < 0.50. Fig. 30 shOws as a function of J0 for different numbers of PID.
5) Propeller Thrust and Torque.
The torque and the thrust of the propeller can be estimated in the same way as for an ordinary proneller, if this has a velocity of advance equal to V. If the propeller thrust is found as the difference between the tota' thrust and the nozzle thrust, the torque can be roughly estimated by regarding a foil which is equivalent to the propeller. The foil has an area A and profile characteristics equal to those of' the propeller at a certain value of x. The exact value of x is
0.10 E 0.08 0.06 0.04 0.02 o Fig. 10
B 4-55 Yc_=oo53
t/c_
FÇ4-55
0.048 VC'.4
C 0.06 0 01 8.2 0.30.4 CL 05
Fig. 11x 0.66 to x 0.78. Usually x 0.70 is chosen as a standard
value. At any section of the foil the velocity w and- the angle of attack are identical to the values that occur at the station x on the propeller blade (Fig. 10).
The llftcoeffisient of the foil is decomposed into the components CQ in the tangential and CTI in the axial direction
(Fig. 10). We get the following equations:
and and 2 t c T n D
KT
nD 2 K T /2 w2 A Q-
pfl'DKQ
(2)i2
2 KQ CQ --p12 w2A.0.35D
p12 w2A .035D w A 0.35 X X CTCLcos
_CDsin
. CQ CL sin + CD CO5 CD O gives KQ1 0.35 tg If CD >0 we get CT KT CL cos - CD sin1 - 0»55 P/D
- Ccos1
CT! Ti L CQ KQCLsin
CD cosC.
K Ql Ql CL sin P/D n QT'
pI2w2A
w A X X1.5 . A IA
Eo
where AE/AQ is the blade area ratio of the propeller.
c is a function of CL, the camber and the thickness of the
profile. In Fig. 11 has been drawn as f(CL)for an actual NACA pröfile. If a more exact expression for CL is wanted, the one on page 13 can be applied.
6) Com2arison between Values Found by Experiment and Calculation. The thrust of the system and the nozzle as well as the torque has been calculated for two fourblacled propellers in nozzle
(l/D z 0.50,
j
z 10.2°). One of the propellers is of the Kaplan type, ('k) the other is a B u-55 propeller (van Manen) (2.3.). Both have the same blade area ratio and the same pitch and pitch distribution (constant). The connection between the hydrodynamicaland the geometrical pitch is indicated by the equation 0.7 tg z
0.96 0.7 tg + 0.055 developed under the assumption of the velocities V + Ux and UT!2 at the propeller disk. is the geometrical angle of pitch. It is assumed that P/D z x tg 6.
is kept constant for different values of x.
For nozzle 6 and 19 (Wageningen, van Manen) (2.'4) Dd/D is put equal to 1.06 and 1.09. The slope of the lift is given by
CL
lo
-If KT, and are known, KQ can be estimated. is a function of CL. Gutsche has analysed a number of propellers calculated
by vortex theory and gives the following formula for a rough estimation of CL K p d C1 z 0.11 L k1, dOE
where k1 is shown in Fig. 6 as function of l/D.
d CL
da 21T k1
120 ,.
a.-'
.h
0.12d110
100__
90lo. -
100_ a
90110g
100 L'-90 80II
lO 20 30 40 50 60 xf/cFigl2a
1.0 0.8 0.6 0.4 0.2 120 d C1 dcx. 110 100 90 110 100 90 110 100 110 loo 10 20 30 40 50 60Fg12b
0 0.6 0.8 1.0 1.2Fig 27
1.4/D
is
4., 0,2 41 44' 43 4 47 ¿3 4. 48
A
-Fig .1 3. 43 48 47 45 0,5 44'ç 43 o8-/nOiscN,'6
m//N4C4-Prv/7/4'75 KpDn
-
742e H -A ilL
,
t
AiI1U1
IUI
1I1I
IiL
ß'#-55 Scrie ni/I N4C4-PrcI)i 0,50 102° thOúc4'r.6 4'4'/5 ¿34' 45 O,6'O,7 0,8 45 1,0 7,1 2 1,3 O 41 42 43 1,3 1' ç' 45 46 47 48 ¿3 0f1-I-O
4 0-5
o
'n
np
Fg.14,
SCREW SERIES IN NOZZLE No.19
H,, 11/)-I.4 2 08
!FILIIIIIk
)l 0-4 171/
-' rL rA -%-
-o OS
-dO
(21T k1).
In Fig. 12a and b we have given dL as function of
the distance between the leading edge and the point of max. camber.in Fig. 12e is the mean of values measured by MACA and CØttingen. For the comparison with B 4-55 the K-values for z 4 are employed directly. In the case of the Ka 4-55 propeller
K for z 5 is employed. By the calculation of KQi
ktg jKTj,
k is chosen as 0.35 for B 4-55 and a bit higher for Ka 4-55.
A comparison between experimental and calculated values shows good agreement (Fig. 13 and 14). The conclusion ìs: The
theory seems applicable for a rough calculation and as base for a simple analysis of the influence of different parameters.
7) Mozzle Wake and Pro2eller Thrust.
It is important to know the velocity through the
propeller disk. This velocity VP is given in percent of VA by the following equation
V
-VA
where
'a is called the nozzle wake. ta iias been estimated by Dickmann and Weissinger for propellers in nozzles with contra systems (no rotation in the slipstream, UT 0). It may also be computed by the formula
0.5 (/1 + 2 C - 1), o where T C ° p12
V2
A oThe formula has been developed from simple momentum consideration. It gives values of the same order of magnitude as those for nozzles without contra systems but is too rough for an accurate calculation.
It does not take into consideration the influence of pitch, as will be seen from Fig. 23 where the formula has been compared to some
-4.0
-3.5
-3.0
- 2.5 -2.0-1.5
-1.0-0.5
o -5.0 -4.5-4.0
-3.5
-3.0 -2.5 -2.0 -1.5-1.0
-0.5
0 5 10 15 20 25 30 35 40 45Fig 23
5 10 15 20 25 30 35 40 45 coFig 24
NACA 415
VD OESB 4-55
«1 =12.70 SI/o 1.4¿I.
,P
D.W./
/ì,-5.0 'V -4.5 -4.0 -3.5 -3.0 -2.5 -2.0 -1.5 -1.0 - 0.5
-5.0
4)-4.5
-4.0 -3.5 -3.0-2.5
- 2.0 -1.5 -1.0 -0.5 o ou
-u
IFA
r'
Alu
IUA
-u
O 5 10 15 20 25 30 3540,-50
Fig.25.
10 15 20 25 30 3540c45
oFig.26.
12
-experimental results obtained by van ianen. (2,
3,
,5).
VA
0.5 + 0.5
<. This was assumed to be correct some distance behindthe nozzle but at the propeller disk Kt will often have a higher value. (Especially in the case of the Kaplan type propeller.)
For Ka
a-55
and nozzle No. 19 it is assumed thatK + K1
\z
I (Fig.27),
2
and for B
a-55
and nozzle No.3 that K= K(z=4).
The equationU
- 1) gives good agreement with
the Wageningen tests as shown in Fig. 23, 224, 25 and Fig. 2G.
At radius r we get the following circulation around the propeller blades
F 2 r UT
According to Kutta Joukowski the propeller thrust will be
d T p 2it r U K (wr - U /2)dr. P T g T Integration gives T 2 UT Kg (wr - UT/2)r dr. o and nondimerisional K UT (wr - U /2)K x dx. t g
2(R)2
U arwas put equal to
K'(P/D/J0 -
1) and K' equal to0.2 0.1 0.2 0.1 O
B 4-55
NACA 4415o(10.2 WJ0.5
0.1 0.203Kp(dia'ì4
Fig 28
K 4-55
NACA 250102
Íf)0.5
/0'
e O 0.1 0.2 0.3 Kp(dici)0.4Fig 29
0.4 Kp 0.3 0.4 Kp 0.313
-As to Kg values are chosen which give good agreement between calculated and measured wake for the case considered. A distribution of circulation equal to optimal distribution for propellers working in open water (without shrouding) has been
chosen. K has been calculated for different pitch ratios and coefficients of advance for the Ka 'k-55 and B u-55 cases. A comparison is made in Fig. 28 and
29.
The agreement is not to bad.8)
Blade Area-Ratio. Fig. 8.3 gives 2ir x K D CT g (cos - coszC
where z Number of bladesD Diameter of the propeller
C Chord of the profile K Goldstein factor
g
V + (wr)2
For x 0.7 and different values of . and
, CL has been
calculated. Then the angle of attack at x 0.7 has been estimated for AL/A 0.0, 0.55, and 0.70.
To obtain as a function of and t/C, the slope of the CL, curve has to be corrected for the curvature of the flow which in the case of the propeller is different from the wellknown 2 dimensional flow of the given section. In
2 dimensional flow the induced velocity in any direction on the section is U2 2 (x/C, x) CL and ur cos
0.8
K00.7
06
05
0.4 0.3 0.204
0.6 0.810
1.2 14 16Fig.30.
0. K0 0. 0.o
o
0.2 0.1/
0.40
0.55
0.70
Fig.31. JJO.2
06
08101214
0. K
0
0. 0. 0.1o
0.406
0.8 1.0 1.2 14 16Fig32.
I I°.
/
1.0 K o 0.9
0.8
0.7 0.605
04
0.3 0.2JQ
À
r
'VA
À
r
lì
7
055
070
0.406
0.8 10 12 14 1.6Fi933,
If the same section is placed on the nropeller the corresponding velocity is
U3 f3 (x/C x)CL.
The difference U U3 - U2 C (f3 - f2) gives the change in effective camber. If CL
O,U =
O and no correction isnecessary. This means that the angle of zero lift remains unchanged for a given camber.
If the lift is different from zero and a certain is wanted for a given section and propeller, the slope of the CL o. curve can be reduced by a value equal to the usual camber correction. There are different methods of calculating the camber correction which all give different values. Ilost of them are only valid for certain distributions of circulation and
for the ideal angle of attack. Further no camber correction has been calculated for the ducted propeller. 'Je therefore have
used a slope reduction of 30 as a mean. Ludwieg Ginzel's camber correction gives a reduction having the same order of magnitude.
By drawing the CL curves for AE/A O.0, 0.55, and
0.70
a has been found for different values of CL, =x Trtg ß andJ0.
Then for AE,A = O.O, 0.55, and 0.70 has been
estimated by setting
a =
-where is given by
X
tg
.From the simple geometrical relation between and sj' K0 has been calculated for different values AE/A and
J0.
Fig.35.
-3
-2
-1 i 23
4
5 67
Fig.34.
- 15
This ha been donc for nozzle No. 7, 3 14_40, B 4-55 and B '4-70. In Fig. 30, 31, 32 the calculations arc represented by the
points and show good correlation with the curves obtained
from experiment. Concerning the Kaplan type propeller results are available from tests with Ka '4-55 and Ka '4-70 in nozzle No. 19A (Nageningen). At x 0,7 the tic ratios are 0,0370 and 0,0482. For circular sections the angle of zero lift is equal to tic. As C0 of the Kaplan propeller is greater than C0
.
of the B type, CL/B will be reduced. At x 0,7 the slope reduction is assumed to be about 14Q corresponding to the
reduction for a B '4-75 propeller. If C0 for the B propeller is 55 it will be 75 for the Kaplan type of equal blade arca
ratio. K0 has also been calculated for K '4-55 and Ka '470
for different values of AE/Ao and J0. As shown in Fig. 33
there is a good correlation between calculated and experimental
References
1) Horn Arntsberg: Entwurf von Schiffsdüsensystemen (Kort-Dysen), Jahrb. S.T.G. Bd. (1950).
Manen, J.D. van:
Manen, J.D. van:
) Manen, J.D. van:
5) Manen-Superina:
Ergebnisse systematischer Versuche mit Schiffsdüsensystemen. Jahrb. S.T.G. Bd. L7 (1953), s. 216 - 2Ll.
Open Water Test Series With Propellers in Nozzles. mt. Shipb. Progress No. 36
(1957), Vol. 4..
Effect of Radial Load Distribution on the Performance of Shrouded Propellers.
Publication No. 209 of the N.S.M.B.
The Design of Screw-Propellers in Nozzles. mt. Shipb. Progress No. 55, Vol. 6 (1959).
Dickmann-Weissinger: Beitrag zur Theorie optimaler Düsenschrauben. Jahrb. S.T.C. Bd. 9 (1955), s. 253-305.
Kobylinski: The Calculation of Nozzle Propeller Systems based on the Theory of thin annular Airfoils with arbitrary Circulation Distribution.
mt. Shipb. Progress No. 88, Vol. 8, (1961). KUchemann-Weber: Aero-Dynamics of Propulsion. Mc. Grw-Hi11.