Abstract
Japan Aerospace Exploration Agency (JAXA) developed a natural laminar flow (NLF) wing design concept to reduce supersonic friction drag for a future SST, and confirmed remarkable transition delay in the flight test conducted in 2005. After the test, stability characteristics on the NLF wing was numerically analyzed in detail, being compared with them on a typical non-NLF wing. The NLF wing has strongly rapid acceleration near leading edge (LE) and then gradual acceleration in chordwise region. Such a chordwise velocity distribution generates rapid decrease of maximum crossflow (C-F) velocity and change of its direction. According to linear stability theory with local parallel flow approximation, this feature contributes to suppress the growth of amplification rates based on the C-F instability.
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