Numerical Investigations of Small-Amplitude Disturbances in a Laminar Boundary Layer with Impinging Shock Waves

Pagella, Alessandro; Rist, Ulrich; Wagner, Siegfried

doi:10.1007/978-3-540-45466-3_19

Cited by 1 publication

(2 citation statements)

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“…For the shock wave, we consider three different shock angles relative to the horizontal axis: ϭ12.5°, ϭ13.2°, and ϭ14°. An earlier validation of the unperturbed flow with impinging shock was performed for M aϭ2 and adiabatic wall, 14,15 where suitable data have been available. The three different shock angles have been chosen to obtain a flow situation, where the boundary layer is still bound to the plate ͑ϭ12.5°͒, a small separation area occurs ͑ϭ13.2°͒, and a large separation bubble ͑ϭ14°͒ appears.…”

Section: A Unperturbed Laminar Boundary Layermentioning

confidence: 99%

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Numerical investigations of small-amplitude disturbances in a boundary layer with impinging shock wave at Ma=4.8

2002

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The stability behavior of a laminar boundary layer with shock boundary layer interaction and small amplitude disturbances is investigated by linear stability theory and direct numerical simulation. By a complex interaction of several physical properties, the impinging shock wave locally influences stability behavior of the boundary layer, dependent on its shock strength, applied disturbance frequency, and disturbance propagation angle with respect to the flow direction (obliqueness angle). Due to the displacement of the boundary layer near shock impingement and the according Reynolds number effect in this area, the boundary layer is locally destabilized. The displacement of the boundary layer also produces an increase of the thickness of local regions of relative supersonic speed, which promotes second mode instability. For the results obtained by direct numerical simulation nonparallel effects could be identified and quantified. Taking these nonparallel effects into account, linear stability theory is able to represent the stability behavior of wall distant disturbance amplitude maxima having small obliqueness angles for the cases investigated here. For larger obliqueness angles and disturbance amplitudes at or close to the wall the agreement between linear stability theory and direct numerical simulation declines considerably.

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Section: A Unperturbed Laminar Boundary Layermentioning

confidence: 99%

“…The numerical scheme, which is based on the works of Thumm, 9 Eißler, 10-12 and Fezer 13 was extended by Pagella 14,15 to investigate shock boundary layer interactions. A two-dimensional base flow is calculated by solving the two-dimensional Navier-Stokes equations.…”

Section: Numerical Schemementioning

confidence: 99%