Abstract
This paper gives a summary of dedicated experiments on the shock interaction induced heat flux augmentation, by means of tests carried out in the hypersonic wind tunnel H2K. The first test case is devoted to the shock boundary layer interaction on a flat plate. The interaction impact has been varied by changing the free stream parameters and the position of the shock generator, i.e. shock impingement point on the plate. The heat flux distribution has been determined using surface temperature data measured by an infrared camera. The heat flux data combined with free stream flow parameters allow calculation of the Stanton number evolution. The second test case is a double sphere configuration with a variable axial and lateral distance between the spheres. This allowed measurements of the heat flux augmentation induced by a shock-shock interaction along the complete frontal surface of the second sphere, which was hit by the bow shock of the first sphere. Shock-shock and shock-boundary layer interaction effects are studied by means of experiments on the IXV flight configuration with double control flaps. Depending on the test configuration and flow parameters, shock interaction induced heat flux augmentation factors up to seven have been measured.Graphical abstract
Highlights
Hypersonic vehicles are exposed to severe aerothermal loads, which may be the main design driver depending on the trajectory parameters
This paper summarizes results of recent experiments concerning the shock induced heat flux augmentation (SIHFA) in the DLR’s hypersonic wind tunnel H2K
This experimental study discussed the role of the Shock Wave—Shock Wave—Interaction (SWSWI) and Shock Wave Boundary Layer Interaction (SWBLI) on the heat flux augmentation in hypersonic flow
Summary
Hypersonic vehicles are exposed to severe aerothermal loads, which may be the main design driver depending on the trajectory parameters. Jaunet et al investigated the influence of the wall temperature effects on the shock induced separation behaviour by using particle image velocimetry and hot-wire technique for experiments at Mach 2.3 (Jaunet et al 2014) Their results indicate the impact of aerothermal heating on the size and low-frequency unsteadiness of shock wave boundary layer interaction (SWBLI). Schülein investigated the shock wave boundary layer interaction by performing heat flux and skin friction measurements on a shock impinged flat plate at Mach 5 (Schülein 2006). The three-dimensional effects of the experiments were declared as the source of deviation between numerical simulations and experiments Another interesting work related to shock induced pressure and heat flux loads has been published by Wang et al (Wang et al 2021).
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