Abstract
Hypersonic boundary-layer stability has significant importance in vehicle design and successful operation. This paper investigates the stabilization effects of local wall cooling on the hypersonic boundary layers over a 5 deg half-angle blunt cone with a nose radius of 0.0254 mm. We employed a high-order-accurate flow solver to calculate the steady flow for a freestream Mach number of 6.0 and a unit Reynolds number of 25.59 × 106 ∕m. In simulations, we considered partial wall cooling, entire wall cooling, and adiabatic wall scenarios. Furthermore, we examined partial cooling parameters such as strip location, length, and temperature profiles. We calculated the growth rates, phase speed, and N-factor diagrams using a linear stability analysis. The results showed that complete wall cooling destabilizes the boundary layer. However, the cooling strip upstream of the synchronization point stabilized the boundary layer by damping the disturbances. The longer cooling strip further stabilized the boundary layer. The cooling strip placed downstream of the synchronization point destabilized the boundary layer.
| Original language | English |
|---|---|
| Pages (from-to) | 412-426 |
| Number of pages | 15 |
| Journal | Journal of Spacecraft and Rockets |
| Volume | 60 |
| Issue number | 2 |
| DOIs | |
| State | Published - Mar 2023 |
| Externally published | Yes |
Funding
We acknowledge that the numerical simulations were performed at Oklahoma State University’s High Performance Computing Center, which is supported in part through National Science Foundation grant OAC–1531128. We also would like to thank the reviewers for taking the time and effort necessary to review the paper. We sincerely appreciate all of their valuable comments and suggestions, which helped us to improve the quality of the paper.