Base pressure in transonic speeds a comparison between theory and experiment

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Abstract

The problem of base pressure in the absence of base bleed has been investigated for a symmetrical model with a square-cut trailing edge. The model was mounted at zero angle of attack in a transonic wind tunnel covering a range of mainstream Mach number from 0.6 to 1.3. The role of vortex shedding was found to be of great importance in the prediction of base pressure. A semi-theoretical analysis for the prediction of base pressure in subsonic and transonic speeds which includes the effect of vortex shedding is proposed.

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APA

Motallebi, F. (1988). Base pressure in transonic speeds a comparison between theory and experiment. In Proceedings of the ASME Turbo Expo (Vol. 1). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/88-GT-132

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