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Summary of Flight-Test Results of the VZ-2 Tilt-Wing AircraftFlight-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.
Document ID
19980227196
Document Type
Other - NASA Technical Note (TN)
Authors
Pegg, Robert J. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1962
Subject Category
Aircraft Design, Testing and Performance
Report/Patent Number
NASA-TN-D-989
L-1574
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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