超音速機首境界層の遷移(安定性・乱流境界層・せん断流・遷移(3),一般講演)

概要

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Boundary layer transition on four axisymmetrical bodies with different pressure gradient, those are a Sears-Haack body, a semi-Sears-Haack body, a sharp cone and a flared cone, was analyzed numerically and experimentally. The aim is understanding of transition mechanism of nose boundary layer transition to design of the supersonic natural laminar flow nose. It is found that the transition on a Sears-Haack body with favorable pressure gradient is most delayed. In addition, transition on low sonic-boom nose was analyzed numerically. It was confirmed that control of cross flow leads suppression of boundary layer transition.
2009-09-02