XV-15 litho - NASA's History Office

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Figure A-11. XV-15 height-velocity envelope. Figure A-12. XV-15 variation of power with airspeed. 130 Rotor shaft horsepower Density altitude, ft × 10 3 2400 2000 1600 1200 800 400 32 28 24 20 16 12 8 4 Level flight 5° Dive 0 40 80 120 160 200 True airspeed, knots Hover Single engine emergency power available Nacelle angle = 90° Flap angle = 20° Conversion corridor torque limit Normal rated power limit Torque limit 335 knots True 240 280 320 360 Symbols Estimated Predicted Flight test data 0 40 80 120 Calibrated airspeed (knots) 160 200 240 60° 20° 30° 20° V ~ true = 300 knots @ 16,000 ft 0° 20° Helicopter mode Airplane mode Airplane torque limit 0° 0°
XV-15 Characteristics Powerplant Two Lycoming LTC1K-41K turboshaft engines (modified T53L13B) Horsepower ratings Contingency (2 minutes). . . . . . . . . . 1802 SHP Takeoff (10 minutes). . . . . . . . . . . . . 1550 SHP Normal (max. continuous) . . . . . . . . 1250 SHP Length . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42 ft 1 in (not including nose boom) Wing Span. . . . . . . . . . . . . . . . . . . . . . . . . . 32 ft 2 in Area. . . . . . . . . . . . . . . . . . . . . . . . . . 169.0 sq ft Chord (constant) . . . . . . . . . . . . . . . . 5.25 ft Airfoil section . . . . . . . . . . . . . . . . . . NACA 64A223 Sweep . . . . . . . . . . . . . . . . . . . . . . . . -6.5 degrees Dihedral. . . . . . . . . . . . . . . . . . . . . . . 2.0 degrees Aspect ratio. . . . . . . . . . . . . . . . . . . . 6.12 Width . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57 ft 2 in (to outer tip of proprotor disc) Height . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12 ft 8 in Horizontal tail Span. . . . . . . . . . . . . . . . . . . . . . . . . . 12ft 10 in Area. . . . . . . . . . . . . . . . . . . . . . . . . . 50.25 sq ft Chord. . . . . . . . . . . . . . . . . . . . . . . . . 3 ft 11 in Airfoil section . . . . . . . . . . . . . . . . . . NACA 64A015 Aspect ratio. . . . . . . . . . . . . . . . . . . . 3.27 Vertical tail Area. . . . . . . . . . . . . . . . . . . . . . . . . . 50.5 sq ft Airfoil section . . . . . . . . . . . . . . . . . . NACA 0009 Mean Aerodynamic Chord . . . . . . . . 3.72 ft Aspect Ratio . . . . . . . . . . . . . . . . . . . 2.33 Proprotor No. of proprotors . . . . . . . . . . . . . . . 2, interconnected Blades/proprotor . . . . . . . . . . . . . . . . 3 Diameter . . . . . . . . . . . . . . . . . . . . . . 25 ft Chord (constant) . . . . . . . . . . . . . . . . 14.0 in Solidity . . . . . . . . . . . . . . . . . . . . . . . 0.089 Disc loading . . . . . . . . . . . . . . . . . . . 13.2 lb/sq ft Twist, geometric (spinner to tip). . . . 36 degrees Delta 3 angle. . . . . . . . . . . . . . . . . . . -15.0 degrees Rotational speed Helicopter mode . . . . . . . . . . . . . . . . 589 rpm Airplane mode. . . . . . . . . . . . . . . . . . 517 rpm 131
Page 1:
The History of The XV-15 Tilt Rotor
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Contents Prologue . . . . . . . . .
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Dedication The story of the success
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Foreword The development of tilt ro
Page 17 and 18:
List of Figures Figure 1 Leonardo d
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Figure 41 Simultaneous static test
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Figure A-2 Transcendental Model 2 t
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List of Acronyms AARL Army Aeronaut
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TRENDS Tilt Rotor Engineering Datab
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Figure 2. Illustration of vertical
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Figure 4. McDonnell XV-1 compound h
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Figure 7. Henry Berliner tiltpropel
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Top: Figure 9. The Baynes Heliplane
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Figure 13. Illustration from the Ha
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Figure 17. Bob Lichten, extreme lef
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Figure 20. Tiedown tests of the XV-
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16 Research and Engineering), obtai
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18 management continued to show int
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20 Building the Technology Base Aer
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Figure 25. Bell 25-ft. diameter pro
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Figure 28. Performance tests of 5-f
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Figure 31. Bell 25-ft. diameter pro
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28 Tilt Rotor Research Aircraft Pro
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30 During the late 1960s and early
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32 range of loading conditions and
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34 The initial projected cost of $4
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Figure 35. Illustration of the Boei
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Figure 36. 1/5 scale XV-15 model in
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40 under the contract. To accomplis
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42 Aircraft Development The primary
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44 Test stand angle box Test stand
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Figure 40. Proprotor response to co
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Figure 41. Simultaneous static test
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50 helicopters. For the conversion
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52 Prior to the start of flight ope
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Figure 44. Initial Bell tiedown sho
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56 degrees 25 and a brief assessmen
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Figure 45. XV-15 in the Ames Resear
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60 NAVAIR managers as a means of de
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Figure 46. Government and Bell pers
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Figure 49. Tiedown test facility at
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66 Wheel height Top: Figure 51. Met
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68 Symmetric beam mode Antisymmetri
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Figure 55. XV-15 during short takeo
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Top: Figure 56. Flow visualization
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74 during “degraded” flight con
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Figure 59. Hover acoustics tests du
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78 Nose weight Top: Figure 61. Typi
Page 106 and 107: 80 Following the completion of cont
Page 108 and 109: 82 After the proprotors stopped, th
Page 110 and 111: 84 sudden stoppage of the right eng
Page 112 and 113: 86 A reconversion to the helicopter
Page 114 and 115: 88 Paris Air Show By early 1981, th
Page 116 and 117: 90 enroute from Farnborough to Fran
Page 118 and 119: Top: Figure 66. Senator Goldwater i
Page 120 and 121: Figure 69. Shipboard evaluations of
Page 122 and 123: Figure 71. XV-15 at the New York Po
Page 124 and 125: 98 Crash (October 16 and 17, 1991).
Page 126 and 127: 100 The End of an Era By the mid 19
Page 128 and 129: Top: Figure 73. XV-15 at the Dallas
Page 130 and 131: 104 management system was very effe
Page 132 and 133: 106 could make use of the same flig
Page 134 and 135: Figure 76. The Bell tilt rotor eagl
Page 136 and 137: 110 demonstrations two years earlie
Page 138 and 139: 112 Future Tilt Rotor Aircraft By t
Page 140 and 141: 114 tiltrotor aircraft program. Thi
Page 142 and 143: 116 Model 1-G Characteristics Power
Page 144 and 145: Figure A-3. Transcendental Model 2
Page 146 and 147: Figure A-4. XV-3 three-view drawing
Page 148 and 149: Figure A-5. XV-3 inboard drawing, s
Page 150 and 151: Nacelle angle (degrees) 124 120 90
Page 152 and 153: Figure A-8. General layout and majo
Page 154 and 155: Figure A-9. Side view inboard profi
Page 158 and 159: 132 Weight Design . . . . . . . . .
Page 160 and 161: 134 WBS LEVEL: Bell Army/NASA I II
Page 162 and 163: 136 US Army Air Mobility Research a
Page 164 and 165: 138 Army/NASA (continued) Staff (19
Page 166 and 167: 140 Appendix C—Chronology 1452-15
Page 168 and 169: 142 1968 Boeing Vertol awarded cont
Page 170 and 171: 144 November, Initial piloted simul
Page 172 and 173: 146 24 March 1982 XV-15 demonstrate
Page 174 and 175: 148 30 July 1987 FAA/NASA/DOD Tilt
Page 176 and 177: 150 21 August 1990 V-22 reached 340
Page 178 and 179: 152 14 June 1993 The Department of
Page 180 and 181: 154 Appendix D—Awards and Records
Page 182 and 183: Figure D-1. Jean Tinsley, first wom
Page 184 and 185: Figure E-3. XV-15 flying by the Sta
Page 186 and 187: Figure E-7. Bell test pilots Roy Ho
Page 188 and 189: Figure E-11. Ken Wernicke, Bell til
Page 190 and 191: 164 Appendix F—Bibliography Tilt
Page 192 and 193: 166 Ball, J. C. “XV-15 Shipboard
Page 194 and 195: 168 Churchill, G. B.; Dugan, D. C.
Page 196 and 197: 170 Edenborough, H. K. “Investiga
Page 198 and 199: 172 Harendra, P. B.; Joglekar, M. J
Page 200 and 201: 174 Kvaternik, Raymond G. “Studie
Page 202 and 203: 176 Magee, J. P.; Pruyn, R. “Pred
Page 204 and 205: 178 Martin, Stanley, Jr.; Erb, Lee
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180 Rutledge, Charles K.; George, A
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182 Tischler, M. B.; Leung, J. G. M
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184 Whitaker, H. L.; Cheng, Yi. “
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186 Daniel C. Dugan Daniel Dugan gr
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188 Carnet, 88 Carpenter, Ron, 91 C
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190 Moffett Airfield, Moffett Field
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Monographs in Aerospace History Lau
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National Aeronautics and Space Admi
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XV-15 litho - NASA's History Office

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