This work focuses on the heat flux characteristics of a hypersonic blunt body with a tangential Mach 3 supersonic cooling film. Experiments were carried out with main flow’s Mach numbers of 6, 7, and 8; total pressure of 15 MPa, and total temperature of 2600 K. The wall surface heat flux was measured under different cooling film pressures. Nanoparticle-based planar laser scattering was used to visualize the flowfield. Results showed that cooling film can effectively reduce surface heat flux of the test model, but the cooling efficiency was continuously weakened along the flow direction; a cooling film with a higher mass flow rate was more effective in protecting the model’s surface; the instability of the boundary layer and the mixing layer accelerated heat exchange between the mainstream, the cooling film, and the model surface.
Experimental Study on the Cooling Film Effectiveness of a Hypersonic Blunt Body
Journal of Thermophysics and Heat Transfer ; 35 , 3 ; 623-626
2021-07-01
Article (Journal)
Electronic Resource
English
Transpiration Cooling Of Hypersonic Blunt Body
NTRS | 1991
|REAL-GAS HYPERSONIC BLUNT-BODY FLOWS
AIAA | 1963
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