Steady characteristics of an aerofoil section in a supersonic shear flow

Steady characteristics of an aerofoil in a two-dimensional supersonic shear flow are analyzed by the singularity method. First, on the assumption of small disturbances, a fundamental solution, which represents a supersonic source, is introduced from an equation for perturbed pressures. The solution is composed of two terms; one contains the same Dirac's delta function as in a uniform supersonic flow and the other represents the interference between a source and vorticities in a shear flow. The thin aerofoil theory is applied in order to analyze characteristics of an aerofoil having a thickness distribution.