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 × 10 6 / 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.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Local Wall Cooling Effects on Hypersonic Boundary-Layer Stability


    Contributors:

    Published in:

    Publication date :

    2022-10-25


    Size :

    15 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English







    Effects of Wall Cooling on Hypersonic Boundary Layer Receptivity over a Cone

    Kara, Kursat / Balakumar, Ponnampalam / Kandil, Osama | AIAA | 2008


    Wall cooling effects on hypersonic boundary layer transition, M(1) =7.5 - 15

    NAGAMATSU, H. / SHEER, JR., R. / WISLER, D. | AIAA | 1986