Unsteady transonic flow behind a shock wave (Q1571322)

The paper is devoted to unsteady perturbations of a steady inviscid flow around a body of revolution with sonic velocity at infinity. An unsteady problem on the flow around a half-body with the generator \(r=Ax^k\) is considered. When \(k<1/4\), the solution is represented as the sum of two terms. The solution obtained is used to investigate the stability domain for steady transonic viscous gas flows around airfoils. On the boundary of the stability domain, the flow becomes periodic and the amplitude of shock-wave oscillation becomes comparable to the airfoil's chord.