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Theoretical stability derivatives of thin sweptback wings tapered to a point with sweptback or sweptforward trailing edges for a limited range of supersonic speedsThe stability derivatives valid for a limited range of supersonic speeds are presented for a series of sweptback wings tapered to a point with sweptback or sweptforward trailing edges. These wings were derived by modifying the trailing edge of a basic triangular wing so that it coincided with lines drawn from the wing tips to the wing axis of symmetry. The stability derivatives were formulated by using the pressure distributions previously obtained for the basic triangular wing for angle of attack, constant vertical acceleration, sideslip, pitching, rolling, and yawing. Explicit expressions are given for the stability derivatives with respect to principal body axes, and conversion formulas are provided for the transformation to stability axes. The results are limited to Mach numbers for which the wing is contained within the Mach cones springing from the vertex and from the trailing edge of the center section of the wing.
Document ID
19930092032
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Malvestuto, Frank S , Jr
Margolis, Kenneth
Date Acquired
September 6, 2013
Publication Date
January 1, 1950
Report/Patent Number
NACA-TR-971
Accession Number
93R21322
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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