National Aerospace Laboratory Space Technology Research Group
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Space Technology Research Group
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
For example in wake flow, remarkable drag reduction occurs nonuniform supersonic flow. This phenomenon is important to avoid collision from behind by separated booster. The most simple model for such flow is a set of two parallel flows with different velocities. Analysis for shock wave transfer between these streams gives a reasonable explanation for the results of experiments in NAL.
超音速後流の二平行流モデルによるロケット分離時の抵抗減少解析
naltr0001367.pdf
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