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Impact of Airfoils on Aerodynamic Optimization of Heavy Lift RotorcraftRotor airfoils were developed for two large tiltrotor designs, the Large Civil Tilt Rotor (LCTR) and the Military Heavy Tilt Rotor (MHTR). The LCTR was the most promising of several rotorcraft concepts produced by the NASA Heavy Lift Rotorcraft Systems Investigation. It was designed to carry 120 passengers for 1200 nm, with performance of 350 knots cruise at 30,000 ft altitude. A parallel design, the MHTR, had a notional mission of 40,000 Ib payload, 500 nm range, and 300 knots cruise at 4000 ft, 95 F. Both aircraft were sized by the RC code developed by the U. S. Army Aeroflightdynamics Directorate (AFDD). The rotors were then optimized using the CAMRAD II comprehensive analysis code. Rotor airfoils were designed for each aircraft, and their effects on performance analyzed by CAMRAD II. Airfoil design criteria are discussed for each rotor. Twist and taper optimization are presented in detail for each rotor, with discussions of performance improvements provided by the new airfoils, compared to current technology airfoils. Effects of stall delay and blade flexibility on performance are also included.
Document ID
20060013267
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Acree, Cecil W., Jr.
(NASA Ames Research Center Moffett Field, CA, United States)
Martin, Preston B.
(Army Aviation Systems Command Moffett Field, CA, United States)
Romander, Ethan A.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 23, 2013
Publication Date
January 1, 2006
Subject Category
Aircraft Design, Testing And Performance
Meeting Information
Meeting: American Helicopter Society Vertical Lift Aircraft Design Conference
Location: San Francisco, CA
Country: United States
Start Date: January 18, 2006
End Date: January 20, 2006
Sponsors: American Helicopter Society, Inc.
Distribution Limits
Public
Copyright
Other

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