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Preliminary Wind-tunnel Tests of Triangular and Rectangular Wings in Steady Roll at Mach Numbers of 1.62 and 1.92Damping-in-roll coefficients for a series of triangular plan-form wings and two rectangular plan-form wings have been obtained from supersonic-tunnel tests. The wings were mounted on a body of revolution and tested at Mach numbers of 1.62 and 1.92.
Document ID
19930084532
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Brown, Clinton E
Heinke, Harry S , R
Date Acquired
August 16, 2013
Publication Date
June 1, 1956
Report/Patent Number
NACA-TN-3740
Report Number: NACA-TN-3740
Accession Number
93R13822
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
DAMPING DERIVATIVES - STABILITY
WINGS, COMPLETE - ASPECT RATIO
MACH NUMBER EFFECTS - COMPLETE WINGS
WINGS, COMPLETE - SWEEP

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