Publication Date:
2019-07-17
Description:
Ultimate tiltrotor performance is constrained by coupled wing/rotor whirl-mode aeroelastic instability. A multifaceted research effort to alleviate those constraints is currently underway at NASA Ames Research Center. Design changes to the XV-15 rotor created large increases in the predicted stability boundary; alternatively, they allowed large increases in pitch-flap coupling (delta-three) for a given stability margin. A wind-tunnel experiment has been proposed to demonstrate the improvements at minimum cost. The design methods are also being applied to the V-22. This report summarizes the results to date for the V-22 and compares them to those for the XV-15. A proposed small-scale wind-tunnel model of the XV-15 proprotor is described.
Keywords:
Aircraft Design, Testing and Performance
Type:
Tiltrotor/Runway Independent Aircraft Technology and Applications Specialists Meeting; Mar 01, 2001; Arlington, TX; United States
Format:
text
