Laminar heat-flux from a cooled plate moving at hypersonic speed
POSTER
Abstract
Heat transfer to a fluid via a laminar compressible boundary-layer flow over a flat plate with sharp leading edge is studied in the hypersonic limit. The interaction between the shock wave and boundary-layer is characterized using the hypersonic interaction parameter χ = M3(C/Re)1/2 where M and Re are the free-stream Mach and Reynolds numbers, respectively, and C is the Chapman-Rubesin constant. To study the heat transfer we solved the Prandtl boundary-layer equations that represent the viscous-layer flow over a cooled wall. For the inviscid-layer we utilized a tangent-wedge approximation. Boundary-layer, wall pressure and shear stress profile were computed. The computational results are used to estimate a steady wall heat flux profile over the plate that is compared with recent results from experiments performed in a Mach 6 wind tunnel.
Distribution is unlimited/Case# AFRL-2024-3482; Cleared 06/28/2024
Distribution is unlimited/Case# AFRL-2024-3482; Cleared 06/28/2024
*This research was supported in part by the Air Force Research Laboratory Wright-Patterson AFB Aerospace Systems Directorate, through the Air Force Office of Scientific Research Summer Faculty Fellowship Program, Contract Numbers FA8750-15-3-6003, FA9550-15-0001, and FA9550-20-F-0005.
Presenters
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Thomas Ward
- University of Virginia
- University of Virginia, Department of Mechanical and Aerospace Engineering, Charlottesville, VA 22904