The Prediction of Helicopter Rotor Hover Performance using a ...

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0' 10 0- 09 0-08 Thrust Coeff iciency/ solid ity 0-0 0- 06 -A Test data , accuracy ±0l°(Ref6) • Theory 8 9 10 Collective pitch, degrees Fig. 14 Rotor thrust coefficient and collective pitch for CH 53A rotor 12
0 8 Present method Strip element -momentum theory CT =00915 o 0-8 04 £. 0-6 R - ^ ^ / \ O 8 l-O Fig.15 Blade angle of incidence distribution for six bladed CH 53 rotor
Page 1: C.P. No. 1341 U PROCUREMENT EXECUTI
Page 4 and 5: CONTENTS 1 INTRODUCTION 3 2 DESCRIP
Page 6 and 7: studies, but the thrust to power re
Page 8 and 9: from strip element theory, where n.
Page 10 and 11: 8 The model rotor used in the exper
Page 12 and 13: 10 The roll up of the tip vortex is
Page 14 and 15: 12 T. = ipjc^n?. -c^u. Q. = ipL.^i-
Page 16 and 17: 14 u. L + 9. - a. + TT4- R i i fir^
Page 18 and 19: 16 strengths. Normally only two or
Page 20 and 21: 18 between two of the published cur
Page 22 and 23: 20 distribution measured near the t
Page 24 and 25: 22 and root cut out of the main rot
Page 26 and 27: 24 the complete range of thrust coe
Page 28 and 29: 26 provided that the two-dimensiona
Page 30 and 31: 28 a. blade incidence distribution
Page 32 and 33: 30 No_. 10 11 12 13 14 16 Author M.
Page 34 and 35: Shaft axis 0-2 0-4 z f 0-6 0-8 •0
Page 36 and 37: Calculate coningangle and set up bl
Page 38 and 39: 001 I 0-010 0009 0-008 0-007 Torque
Page 40 and 41: Blode load hi/mm 7 o Flight test, t
Page 42 and 43: U*VJ 1 Q 001 5 0014 0-013 OO12 OOi
Page 44 and 45: Torque 0-008 0-007 0-0 06 coefficie
Page 46 and 47: 0-0007 00006 Power coefficient 0000
Page 50 and 51: 0-0075 0-0070 0- 0065 0-0060 Torque
Page 52 and 53: 0-0075 0-0070 0*0065 0-0060 Torq,ue
Page 56: © Crown copyright 1976 Published b

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