| Abstract: | The characteristics of travelling perturbations of density in a hypersonic shock layer on a flat plate for the Mach number
M∞=21 and unit Reynolds numberRe
1=6·105 m−1 were experimentally studied by the method of electron-beam fluorescence. The perturbations were generated by interaction
of the shock layer behind an oblique gas-dynamic whistle and the leading edge of the plate. The cases of unsteady and quasi-steady
interaction were considered. In both cases, vortex disturbances of finite amplitude were generated. The measurements were
performed at the fundamental frequency F=0.6·10−4 and at the harmonic; the streamwise phase velocities, the growth rates of the disturbances, and the angles of wave propagation
were obtained. The measurement results are compared with some experimental data for subsonic flows, some particular results
of the linear stability theory for compressible flows, and the results obtained on the basis of a simple model of the nonlinear
stage of disturbance evolution in a hypersonic boundary layer.
Institute of Theoretical and Applied Mechanics, Siberian Division, Russian Academy of Sciences, Novosibirsk 630090. Translated
from Prikladnaya Mekhanika i Tekhnicheskaya Fizika, Vol. 40, No. 6, pp. 41–47, November–December, 1999. |
