COMPUTATIONAL ANALYSIS OF THE FLOW PHYSICS OVER A RECTANGULAR OPEN CAVITY WITH VARYINGS SHOCK IMPINGEMENTS

Tanmay B. B. GHOLAP, Majella Riona R., Adithya M., Deepthi Chowdary BOLLA, Devabrata SAHOO

Abstract


In aviation, open cavities have a critical role in influencing performance characteristics. Components such as combustion chamber, landing gear, and weapon bays contain a cavity influenced by the shear layer. Supersonic conditions of cavity flows are a prerequisite for the configuration of missiles and future aerospace vehicles. In the present research, the stream passing above a rectangular open pit containing a shear layer is computationally studied after the impingement of an oblique shock wave generated by a wedge type shock generator. The cavity duct investigated in the present study has a length to depth ratio of 3 at zero degrees angle of attack. Investigation on the influence of flow characteristics such as the magnitude of drag, pressure distribution, and recirculation within the duct has been performed and analyzed for cases in the presence and absence of shock generator at Mach 3. No particular disruption of the shear layer occurs in the absence of an oblique shock. However, a robust recirculation in the shock impingement cases is observed. The shear layer lifts up due to the thrust force generated in the open cavity on the impingement of a shock wave. A strong rear shock is generated at the rear wall separation point of the open duct. Further, the effect of the rise in the strength of the impinging shock on the entire flow over the cavity is also investigated. As the strength of impinging shock increases, it was observed that the magnitude of pressure distribution on the cavity surface also increases.

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References


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