Transition between the regular and Mach shock interaction regimes initiated by a temperature disturbance

The results of searching numerically temperature disturbances which make it possible to convert flow from the steady-state Mach to regular shock interaction when both regimes may coexist simultaneously are given. The flow sensitivity to the temperature variations is calculated by solving the adjoint equations. The control perturbation is sought using gradient methods. The numerical experiments show that transition from the regular to Mach regime can be realized over the Mach number range from 3.45 to 6 by means of an increase in the temperature. Transition from the Mach to regular regime requires to decrease the temperature, it is possible for moderate Mach numbers and cannot be realized for the higher Mach numbers.