Skin Friction and Heat Flux Measurements in Shock/Boundary Layer Interaction Flows

AIAA Journal ◽  
2006 ◽  
Vol 44 (8) ◽  
pp. 1732-1741 ◽  
Author(s):  
Erich Schülein
Keyword(s):  
Boundary Layer ◽  
Heat Flux ◽  
Skin Friction ◽  
Layer Interaction ◽  
Shock Boundary Layer Interaction ◽  
Boundary Layer Interaction ◽  
Flux Measurements

scholarly journals Effects of Crack on Heat Flux in Hypersonic Shock/Boundary-Layer Interaction

2010 ◽  
Vol 58 (674) ◽  
pp. 68-75
Author(s):  
Hiroshi OZAWA ◽  
Katsuhisa HANAI ◽  
Keiichi KITAMURA ◽  
Koichi MORI ◽  
Yoshiaki NAKAMURA
Keyword(s):  
Boundary Layer ◽  
Heat Flux ◽  
Layer Interaction ◽  
Shock Boundary Layer Interaction ◽  
Boundary Layer Interaction ◽  
Hypersonic Shock

scholarly journals Effect of wall temperature on separation bubble size in laminar hypersonic shock/boundary layer interaction flows

2019 ◽  
Vol 11 (11) ◽  
pp. 168781401988555 ◽  
Author(s):  
Amjad A Pasha ◽  
Khalid A Juhany
Keyword(s):  
Boundary Layer ◽  
Heat Flux ◽  
Mach Number ◽  
Wall Temperature ◽  
Separation Bubble ◽  
Layer Interaction ◽  
Shock Boundary Layer Interaction ◽  
Boundary Layer Interaction ◽  
Hypersonic Shock ◽  
Bubble Length

At hypersonic speeds, the external wall temperatures of an aerospace vehicle vary significantly. As a result, there is a considerable heat transfer variation between the boundary layer and the wall of the hypersonic vehicle. In this article, numerical computations are performed to investigate the effect of wall temperature on the separation bubble length in laminar hypersonic shock-wave/boundary-layer interaction flows over double-cone configuration at the Mach number of 12.2. The flow field is described in detail in terms of different shocks, expansion fans, shear layer and separation bubble. The variation of the Prandtl number has a negligible effect on the flow field and wall data. A specific heat ratio of less than 1.4 results in the better prediction of wall pressure and heat flux in the shock/boundary-layer interaction region. It is observed that as the wall temperature is increased, the separation bubble size and hence the separation shock length increases. The high firmness of the laminar boundary-layer at a high Mach number shows that the wall temperature in the shock/boundary-layer interaction region has little effect. The peak wall pressure and heat flux decrease with an increase in wall temperature. An estimation is developed between separation bubble length and wall temperature based on the computed results.

scholarly journals Shock interaction induced heat flux augmentation in hypersonic flows

2021 ◽  
Vol 62 (12) ◽  
Author(s):  
Ali Gülhan ◽  
Sebastian Willems ◽  
Dominik Neeb
Keyword(s):  
Boundary Layer ◽  
Heat Flux ◽  
Free Stream ◽  
Test Case ◽  
Shock Interaction ◽  
Test Configuration ◽  
Layer Interaction ◽  
Flow Parameters ◽  
Shock Boundary Layer Interaction ◽  
Boundary Layer Interaction

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

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