Hypersonic Interaction of a Vortex Wake with a Bow Shock Wave
Shock/Vortex Interaction is one of the fundamental problems of aerogasdynamics, which has been adequately studied neither theoretically nor experimentally [1, 2].
One of the main features of the vortex-shock interaction is its severe unsteadiness. It is experimentally observed in fluctuations of gas-dynamic parameters of the flow and changes in the flow structure and the size of the interaction region. Experimental data with quantitative estimates of manifestations of unsteadiness are rather limited. The absence of numerical and experimental data for hypersonic velocities should be specially noted. Obtaining results for this range of velocities is extremely important for the development of promising flying vehicles (avoiding of catastrophic operation regimes of a hypersonic inlet and improvement of mixing in the combustor).
KeywordsShock Wave Mach Number Vortex Core Vortex Wake Vortex Breakdown
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- 3.Shevchenko, A.M., Shmakov, A.S.: Experimental techniques and results of investigations of an unsteady flowfield in wing wakes / bow shock wave interactions. In: Proc. at XIV Int. Conference for Aerospace Sci., Novosibirsk, June 30-July 6, Section 4, 10 p (2008), ISBN 978-5-98901-040-0Google Scholar