Abstract
Various technologies used to obtain hypersonic gas flows (nitrogen or air) in aerodynamic research of aircraft models designed for various purposes and scramjet elements, which ensure the possibility of modeling close-to-natural flight conditions in hypersonic wind tunnels (HWTs) at Mach numbers ranging from 5 to 25, are considered. Schemes of short-duration HWTs based on pressure multipliers for implementation of these technologies are presented. The principal issues related to determining the required characteristics of HWT elements at high and super-high pressures of the test gas are described. The capabilities of the various HWT schemes are estimated. It is shown that the proposed HWTs with stagnation pressures up to 10 kbar, flow diameter in the test section equal to 1 m, and moderate temperatures in the heaters used in test gas preheating offer the possibility of aerodynamic testing in the range of Mach numbers from 5 to 25 with simultaneous modeling of flight conditions in terms of Reynolds numbers up to 107–109, and also Mach numbers with elevated values of the flow velocity, density, static pressure, static temperature, and dynamic pressure with test duration from 0.1 to 1 s and above. The data reported in the present paper can serve as a scientific basis for the development of industrial HWTs with pressure multipliers for modeling flight conditions at high Mach and Reynolds number values.
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