An experimental research program conducted on a series of tilt rotors designed for a range of blades twist is reported. The test facilities used in the program are identified. The objective of the program was to obtain precise results on the influence of blades twist and aeroelasticity on tilt rotor performance from hover to high speed cruise Mach number to 0.7. Five aluminum rigid rotors and one fiber glass composite rotor were tested.
A summary of wind tunnel research on tilt-rotors from hover to cruise flight
01.02.1973
Sonstige
Keine Angabe
Englisch
COMPACT WIND TUNNEL FOR FLIGHT AND HOVER CAPABILITIES
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