Two-dimensional boat-tailed bases in supersonic flow

Viswanath, P. R. ; Narasimha, R. (1974) Two-dimensional boat-tailed bases in supersonic flow Aeronautical Quarterly, 25 . pp. 210-225. ISSN 0001-9259

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Boat-tailing of aft bodies may affect the base pressure through two mechanisms: firstly by changing the angle between the approaching flow at separation and the reattachment surface, and secondly by distorting the boundary layer through the favorable pressure gradient. The first effect is isolated by tests on inclined backward-facing steps with a fully developed turbulent boundary layer at separation, at free-stream Mach numbers of 1.75 and 2.4. It is found that the base pressure increases significantly with boat-tail angle; the data have been correlated taking explicit account of the boundary layer effect, modifying and extending the approach adopted by Nash (1967). Some of the earlier data on boat-tailed bases, on reexamination in the light of the present correlation, suggest that strongly distorted boundary layers at separation affect the base pressure appreciably.

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