Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.

Theoretical pressure distributions on nonlifting circular-arc airfoils in two-dimensional flows with high subsonic free-stream velocity are found by determining approximate solutions, through an iteration process, of an integral equation for transonic flow proposed by Oswatitsch. The integral equation stems directly from the small disturbance theory for transonic flow. This method of analysis possesses the advantage of remaining in the physical, rather than hodograph, variables and can be applied to airfoils having curved surfaces. After discussion of the derivation of the integral equation and qualitative aspects of the solution, results of calculations carried out for circular-arc airfoils in flows with free-stream Mach numbers up to unity are described.