On the construction and calculation of optimal nonlifting critical airfoils (Q1261811)

Numerical calculations are carried out in the hodograph plane to construct optimal critical airfoil shapes and the flow about them. These optimal airfoil shapes give the highest free-stream Mach number \(M_ \infty\) for a given thickness ratio \(\delta\) and tail angle \(\theta_ T\) (nonlifting) for which the flow is nowhere supersonic. A relationship between \(M_ \infty\) and \(\delta\) for various \(\theta_ T\) is given. Analytical and numerical solutions to the same problem are found on the basis of transonic small-disturbance theory.