Boundary-layer transition on axisymmetric bodies at a nonzero angle of attack in Mach 2 supersonic flow was investigated using experimental measurements and linear stability analysis. Transition over four axisymmetric bodies (namely, the Sears-Haack body, the semi-Sears-Haack body, the straight cone, and the flared cone) with different axial pressure gradients was measured in two different facilities with different unit Reynolds numbers. The semi-Sears-Haack body and flared cone were designed specifically to achieve a broader range of axial pressure distributions. Measurements revealed a dramatic effect of body shape on transition behavior near the leeward plane of symmetry. For a body shape with an adverse pressure gradient (that is, a flared cone), the measured transition patterns show an earlier transition location along the leeward symmetry plane in comparison with the neighboring azimuthal locations. For a nearly zero pressure gradient (that is, the straight cone), such leeward-first transition is observed only at the larger unit Reynolds number. Finally, transition occurs farther downstream along the leeward plane for the remaining two body shapes with a favorable pressure gradient. The observed transition patterns are partially consistent with the numerical predictions based on linear stability analysis. Presented as Paper 2012-3259 at the 42nd AIAA Fluid Dynamics Conference and Exhibit, New Orleans, 25 May-28 June 2012
Pressure Gradient Effects on Supersonic Transition over Axisymmetric Bodies at Incidence
AIAA journal ; 53 , 12
2015
Aufsatz (Zeitschrift)
Englisch
TRANSITION WITHIN LEEWARD PLANE OF AXISYMMETRIC BODIES AT INCIDENCE IN SUPERSONIC FLOW
British Library Conference Proceedings | 2012
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