Calculation of pressure distribution along spanwise strip of airfoil due to angle of attack along second spanwise strip; results of earlier papers used to calculate lift and moment coefficients for rectangular airfoil that experiences sudden change in angle of attack (without rotation) in otherwise uniform supersonic stream or which enters sharp edged gust; results are valid when Mach lines from leading edge corners do not intersect opposite side edges; curves.
Transient loading of supersonic rectangular airfoils
J Aeronautical Sciences
Journal of the Aeronautical Sciences ; 17 , n 10
1950
6 pages
Article (Journal)
English
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