Study of interference of two roughness wakes for compressible flow

Laminar-turbulent transition on the blunt leading edge generated by roughness can lead to a sharp growth of heat fluxes on the surface of hypersonic vehicles. Experimental study of the roughness was performed in the T-327b at M = 5, Re1 ≈ 3·106 1/m and radius of bluntness R = 9 mm. Two types of roug...

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Bibliographic Details
Main Authors: Polivanov, P. A., Gromyko, Yu. V., Maslov, A. A.
Format: Conference Proceeding
Language:English
Subjects:
Compressible flow
Data analysis
Fluid dynamics
Heat flux
Hypersonic vehicles
Laminar flow
Mass flow rate
Roughness
Wakes
Wall temperature
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Summary:Laminar-turbulent transition on the blunt leading edge generated by roughness can lead to a sharp growth of heat fluxes on the surface of hypersonic vehicles. Experimental study of the roughness was performed in the T-327b at M = 5, Re1 ≈ 3·106 1/m and radius of bluntness R = 9 mm. Two types of roughness were considered: isolated, and combination of two single roughnesses. Nonstationary measurements of mass flow rate and measurement of wall temperature were performed. The effect of the roughness geometry on the laminar-turbulent transition was studied. Data analysis showed the main features of the flow around the roughness.
ISSN:0094-243X
1551-7616
DOI:10.1063/1.5065321