Skin Friction Reduction of Hypersonic Body by Supersonic Layer.
- Resource Type
- Article
- Authors
- Zhao, X. H.; Yi, S. H.; Mi, Q.; Hu, Y. F.; Ding, H. L.
- Source
- Fluid Dynamics. Oct2022, Vol. 57 Issue 5, p686-696. 11p.
- Subject
- *COMPUTATIONAL fluid dynamics
*FRICTION
*WIND tunnel testing
*SUPERSONIC flow
*FLOW visualization
*DRAG force
*JETS (Fluid dynamics)
*SPEED
- Language
- ISSN
- 0015-4628
Both numerical methods and wind tunnel tests were used to reduce skin friction for a hypersonic body. A hypersonic cone was tested under three different free-stream flow conditions using computational fluid dynamics (CFD). A Mach 2.6 annular tangential jet was produced to cover the surface of the cone. The pressure field shows that the supersonic jet is able to reduce spatial pressure difference. The calculated velocity field shows that the supersonic jet produces a lower speed layer near the wall of the model. Flow visualization results from nano-tracer-based planar laser scattering (NPLS) proves that this supersonic flow exists on the surface at a relatively long distance. The drag force results based on CFD and wind tunnel tests prove that the supersonic flow can obviously reduce the skin friction being affected by the shearing strength between the main flow and the supersonic jet. Based on the results of this study, it is certificated that the supersonic layer is capable to reduce skin friction due to reducing the boundary speed. [ABSTRACT FROM AUTHOR]