Wing Download Results from a Test of a 0.658‐Scale V‐22 Rotor and Wing
Abstract:A test of a 0.658‐scale V‐22 rotor and wing was conducted in the 40×80 Foot Wind Tunnel at Ames Research Center. One of the principal objectives of the test was to measure the wing download in hover for a variety of test configurations. The wing download and surface pressures were measured for a wide range of thrust coefficients, with five different flap angles, two nacelle angles, and both directions of rotor rotation. This paper presents these results, and describes a new method for interpreting wing surface pressure data in hover. This method shows that the wing flap can produce substantial lift loads in hover.
Document Type: Research Article
Affiliations: NASA Ames Research Ctr., Moffett Field, Calif.
Publication date: October 1, 1992
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