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

Max A. Heaslet, John R. Spreiter
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.

An Adobe Acrobat (PDF) file of the entire report: