Characteristics of thin triangular wings with triangular-tip control surfaces at supersonic speeds with Mach lines behind the leading edge

Warren A. Tucker
naca-tn-1600
May 1948


A theoretical analysis, based on the linearized equation for supersonic flow, was made of the characteristics of triangular-tip control surfaces on thin triangular wings. By restricting the analysis to the case for which the Mach lines from the wing aper lie behind the leading edge, a simplified treatment was made possible in that the results of previous work on the lift of triangular wings could be used to derive simple expressions for the lift effectiveness, pitching moment, rolling-moment effectiveness, and hinge moment due to control deflection.

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