Computational and Experimental Research of the High-Speed Gas Flow Structure Near Aircraft Fragments Models

The study shows the results of calculation and experimental studies of shock-wave configurations formed during the high-speed gas flow of aircraft fragments models at Mach numbers M = 4-8. We performed a series of experiments with models - semiwedges having single and double apex angles, as well as sharp and blunted edges. The article describes technical works aimed at increasing the accuracy of experimental research. The study also gives the results of modeling by means of the developed author's code of gas dynamic processes fixed experimentally. Finally, we estimate the use of experimental results for validation of the developed calculation codes.

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