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Summary of Flight-Test Results of the VZ-2 Tilt-Wing Aircraft
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Author and Affiliation:
Pegg, Robert J.(NASA Langley Research Center, Hampton, VA United States)
Abstract: Flight-test information gained from a tilt-wing research aircraft tested at the Langley Research Center has shown that design problems exist in such fields as low-speed stability and control, handling qualities, and flow separation during transition. The control power in the near-hovering configuration was considered by the pilots to be inadequate in yaw, marginal in pitch, and excessive in roll. Solutions for some of the design problems are indicated; for example, the addition of a leading-edge droop to the wing in an attempt to delay flow separation resulted in such significantly improved handling qualities in the transition range that an additional descent capability of 1,100 feet per minute was obtained.
Publication Date: Feb 01, 1962
Document ID:
19980227196
(Acquired Oct 31, 1998)
Subject Category: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number: NASA-TN-D-989, L-1574
Document Type: Technical Report
Financial Sponsor: NASA; Washington, DC United States
Organization Source: NASA Langley Research Center; Hampton, VA United States
Description: 44p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: FLIGHT TESTS; BOUNDARY LAYER SEPARATION; VZ-2 AIRCRAFT; SEPARATED FLOW; DESIGN ANALYSIS; LEADING EDGES; HOVERING; CONTROLLABILITY; STABILITY; ROLL; YAW; RESEARCH AIRCRAFT
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