Technical Memorandum of National Aerospace Laboratory
巻
326
ページ
18
発行年
1977-03
抄録（英）
A numerical calculation of the supersonic flow of a perfect gas over conical flare was performed for mach number range between 1.2 to 10.0. The characteristic method was emp'oyed. The method was found useful for conical flares with slope abnormalities, non- linear effect were also investigated.
超音速に於ける円錐フレヤー上の圧力係数
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