Wave processes in the shock layer on a flat plate at an angle of attack
A numerical and experimental study of receptivity of the viscous shock layer on a flat plate aligned at an angle of attack to external acoustic perturbations is performed. Density and pressure fluctuations are measured in experiments at the free-stream Mach number M ∞ = 21 and Reynolds number Re 1 = 6·10 5 m −1 . Direct numerical simulations of receptivity of the viscous shock layer to external acoustic perturbations in wide ranges of the governing parameters are performed by solving the Navier-Stokes equations with the use of high-order shock-capturing schemes. The calculated intensities of density and pressure fluctuations are found to be in good agreement with experimental data. Results of the study show that entropy-vortex disturbances dominate in the shock layer at small angles of attack, whereas acoustic perturbations prevail at angles of attack above 20°.
Key wordshypersonic flows shock layer receptivity direct numerical simulations experiment
Unable to display preview. Download preview PDF.
- 3.A. A. Maslov, A. N. Kudryavtsev, S. G. Mironov, et al., “Control of disturbances in a hypersonic shock layer on a flat plate by an unsteady action from the surface,” Izv. Ross. Akad. Nauk, No. 3, 152–161 (2008).Google Scholar
- 7.S. A. Gaponov and A. A. Maslov, Development of Disturbances in Compressible Flows [in Russian], Nauka, Novosibirsk (1980).Google Scholar
- 9.X. Zhong, “Receptivity of hypersonic boundary layers to freestream disturbances,” AIAA Paper No. 2000-0531 (2000).Google Scholar
- 10.I. V. Egorov, V. G. Soudakov, and A. V. Fedorov, “Numerical simulation of receptivity of a supersonic boundary layer to acoustic disturbances,” Izv. Ross. Akad. Nauk, Mekh. Zhidk. Gaza, No. 1, 42–53 (2006).Google Scholar