24th Congress of International Council of the Aeronautical Sciences, 29 August-3, September 2004, Yokohama, Japan
Paper ICAS 2004-2.8.2

THREE DIMENSIONAL BOUNDARY LAYER TRANSITION ANALYSIS IN SUPERSONIC FLOW USING A NAVIER-STOKES CODE

Y. Ueda, H. Ishikawa, K. Yoshida
Japan Aerospace Exploration Agency (JAXA), Tokyo, Japan

Keywords: CFD, NS, 3-D boundary layer, T-S instability, cross-flow instability, sharp cone

The authors tried to improve the accuracy of transition analysis in supersonic flow by combining a usual e^N method and a Navier- Stokes computation. Transition characteristics of a sharp cone and a nose cone with non-zero angle of attack, and a supersonic natural laminar flow (NLF) wing designed by our agency were analyzed.

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