Three-dimensional transonic flow theory applied to slender wings and bodies

Max A. Heaslet, John R. Spreiter
naca-report-1318
Jan 1957


The present paper re-examines the derivation of the integral equations for transonic flow around slender wings and bodies of revolution, giving special attention to conditions resulting from the presence of shock waves and to the reduction of the relations to the special forms necessary for the discussion of sonic flow, that is, flow at free-stream Mach number 1.

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