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High-Speed Wind-Tunnel Tests of Dive-Recovery Flaps on a 0.3-Scale Model of the P-47D AirplaneThis report presents the results of tests of a 0.3-Scale Model of the Republic P-47D airplane equipped with several dive-recovery flaps. Results are presented showing the drag coefficient and pitching-moment coefficient produced by the various flaps. The results of computations made to predict the normal acceleration due to deflecting the flaps in a vertical dive, the lift coefficient of the tail required for balance, and the relative magnitudes of the various factors which contribute to the pitching-moment increment are also given.
Document ID
20150019985
Acquisition Source
Langley Research Center
Document Type
Other - Technical Report
Authors
William T Hamilton
( Ames Aeronautical Laboratory Moffett Field, CA, United States)
Lee E Boddy
( Ames Aeronautical Laboratory Moffett Field, CA, United States)
Date Acquired
October 29, 2015
Publication Date
May 1, 1945
Subject Category
Aerodynamics
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-ACR-5D19
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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