Method for Calculation of Pressure Distributions on Thin Conical Bodies of Arbitrary Cross Section in Supersonic Stream

摘要

An approximated method is presented for calculating the pressure distribution on conical bodies of noncircular cross section in a supersonic flow field. By a superposition of elementary conical flows due to line sources, the flow about an arbitrary cone may be described. Illustrations of the pressure distribution about several shapes are included to demonstrate the method. The problem of such a body at angle of attack may also be solved by the same method, as well as the problem of yawed flight at angle of attack.