Journal Article Pressure Gradient Effects on Supersonic Transition over Axisymmetric Bodies at Incidence

Tokugawa, Naoko  ,  Choudhari, Meelan  ,  Ishikawa, Hiroaki  ,  Ueda, Yoshine  ,  Fujii, Keisuke  ,  Atobe, Takashi  ,  Li, Fei  ,  Chang, Chau-Lyan  ,  White, Jeffery  ,  徳川, 直子  ,  Choudhari, Meelan  ,  石川, 敬掲  ,  上田, 良稲  ,  藤井, 啓介  ,  跡部, 隆  ,  Li, Fei  ,  Chang, Chau-Lyan  ,  White, Jeffery

53 ( 12 )  , pp.3737 - 3751 , 2015-09-03 , American Institute of Aeronautics and Astronautics
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.
Physical characteristics: Original contains color illustrations
形態: カラー図版あり

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