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Comparison of Space Shuttle Orbiter low-speed static stability and control derivatives obtained from wind-tunnel and approach and landing flight testsTests were conducted in the 8 foot transonic pressure tunnel to obtain wind tunnel data for comparison with static stability and control parameters measured on the space shuttle orbiter approach and landing flight tests. The longitudinal stability, elevon effectiveness, lateral directional stability, and aileron effectiveness derivatives were determined from the wind tunnel data and compared with the flight test results. The comparison covers a range of angles of attack from approximately 2 deg to 10 deg at subsonic Mach numbers of 0.41 to 0.56. In general the wind tunnel results agreed well with the flight test results, indicating the wind tunnel data is applicable to the design of entry vehicles for subsonic speeds over the angle of attack range studied.
Document ID
19810004555
Document Type
Technical Publication (TP)
Authors
Freeman, D. C., Jr. (NASA Langley Research Center Hampton, VA, United States)
Spencer, B., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1980
Subject Category
AIRCRAFT STABILITY AND CONTROL
Report/Patent Number
NASA-TP-1779
L-13945
Funding Number(s)
PROJECT: RTOP 506-51-33-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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