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

More documents

Recommendations

Info

30 No_. 10 11 12 13 14 16 Author M.J. Riley P. Brotherhood J. Scheiman A.R. Mettam R.J. Marshall N. Gregory P.G. Wilby C.V. Cook 15 P.G. Wilby C.V. Cook REFERENCES (concluded) Title, etc. Comparative performance measurements of two helicopter blade profiles in hovering flight. RAE Technical Report 74008 (ARC 35289) (1974) A tabulation of helicopter blade differential pressures, stresses, and motions as measured in flight. NASA TM-X 952 (1964) 24ft tunnel tests of a Wessex tail rotor with variable fin blockage. RAE Technical Memorandum Aero 1028 (1967) NPL 9615 and NACA 0012. A comparison of aerodynamic data. ARC CP 126 1 (1973) Rotor performance prediction in hover. Westland Helicopters Ltd., Research Paper 357 (1968) Effect of production modifications to rear of Westland Lynx rotor blade on sectional aerodynamic characteristics. RAE Technical Report 73043 (ARC 34835) (1973) The structure of the rotor blade tip vortex. Paper 3 in The aerodynamics of rotary wings, AGARD CP 111 (1972)
* max ^n+i~r*| Fjg.l Bound and trailing vortex strength distributions and initial wake
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 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 48 and 49: 0' 10 0- 09 0-08 Thrust Coeff icien
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

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

Create successful ePaper yourself

Delete template?

Save as template?