An experimental research program has been conducted on a series of tilt rotors designed for a range of blade twist in various wind tunnel facilities. The objective was to obtain precise results on the influence of blade twist and aeroelasticity on tilt rotor performance, from hover to high speed cruise Mach number of about 0.7. global forces on the rotor, local loads and blade torsional deflection measurements were compared with theoretical predictions inside a large Reynolds-Mach envelope. Testing techniques developed during the program are described. (Author)
A Summary of Wind Tunnel Research on Tilt Rotors from Hover to Cruise Flight
1972
20 pages
Report
No indication
English
Active Twist and Passive Rotors in Hover and Level Flight
British Library Conference Proceedings | 2023
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