Supersonic flow control

Verma, SB and Hadjadj, A (2015) Supersonic flow control. Shock Waves, 25 (5). pp. 443-449. ISSN 09381287

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Shock wave-induced boundary layer interactions are unavoidable in high-speed flows. The strong adverse pressure gradient imposed by the shock on the incoming undisturbed boundary layer may result in flow separation that is associated with low-frequency oscillations of the separation shock. The separation phenomenon, therefore, leads to undesirable effects such as wall pressure loading, high local wall heating, increased drag coefficient, reduced mass flow ingestion, lower-pressure recovery and inlet unstart conditions.

Item Type: Article
Subjects: ENGINEERING > Fluid Mechanics and Thermodynamics
Depositing User: Mrs SK Pratibha
Date Deposited: 26 Jun 2018 10:08
Last Modified: 26 Jun 2018 10:08

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