2D simulation of interaction between separation region and gasdynamic perturbation caused by rapid heat release in supersonic airflow

Abstract

2D modeling of rapid local release of thermal energy (0.1 – 7 J/m) into the supersonic airflow (Mach number M=2) was carried out in order to change the flow pattern around the wing model. It was shown that the results of numerical simulation of the process of a single instantaneous local heat release on the surface of the model are in good agreement with the experimentally obtained patterns of the flow around the wing model when energy was released using long spark discharge. The simulation of the process of local rapid energy deposition in a pulse-periodic mode was carried out and it was shown that, on the average over time, it is possible to significantly reduce the separation region size. In this case the calculated aerodynamic coefficients of the model change by several percent. It was found that the right choice value of frequency is important, since at an inappropriate value, the effect may be the opposite. It was shown that the stability of the repetition rate of local energy inputs is also important for the shift of the separation point downstream. The mechanisms of the effect of rapid local energy input on the separation region at relatively low and high values of thermal energy are discussed.