Stability of regular and Mach reflection wave configurations in steady flows

Shockwaves are present in a flow as soon as the Mach number becomes supersonic. Being viscous phenomena, Shockwaves are a source of drag which can be predominant when the Mach number is significantly higher than one. In supersonic air intakes, the production of entropy by shocks is felt as a loss in efficiency. At high Mach numbers, Shockwaves produce a considerable temperature rise leading to severe heating problems, complicated by real gas effects. The intersection - or interference - of two shocks gives rise to complex wave patterns containing slip-lines and associated shear layers whose impingement on a nearby surface can cause detrimental pressure and heat transfer loads. The impact of a Shockwave on a boundary layer is the origin of strong viscous interactions which remain a limiting factor in the design of transonic wings, supersonic air intakes, propulsive nozzles and compressor cascades. More effort is needed to improve prediction of these interactions and to devise new techniques to control such phenomena.

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Experiments on shock wave reflection transition and hysteresis in low-noise wind tunnel

Иванов

Kudryavtsev

Nikiforov

et al. 2003

Physics of Fluids

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Experiments on the transition between steady regular and Mach reflections of shock waves have been performed in a low-noise wind tunnel. Owing to a very low level of free-stream disturbances inherent in this facility, the hysteresis phenomenon has been observed in close agreement with theoretical predictions and results of the previous numerical simulations. When increasing the incident shock wave angle, regular reflection persists in most of the dual solution domain. Thus, the detachment criterion can be considered as a true one for the transition from regular to Mach reflection, and an earlier transition observed in many wind tunnel experiments is certainly caused by free-stream disturbances, which were present in those facilities.

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Stability of regular and Mach reflection wave configurations in steady flows

Cited by 6 publications

References 3 publications

Type III and type IV shock/shock interferences: theoretical and experimental aspects

Type III and type IV shock/shock interferences: theoretical and experimental aspects

Shock phenomena in high speed aerodynamics: still a source of major concern

Experiments on shock wave reflection transition and hysteresis in low-noise wind tunnel

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