Numerical Design of a Shockless Transonic Quasi-Aircraft

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概要

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• In order to design a shock-free aircraft in a transonic flow, a numerical simula-lion is carried out on a three-dimensional flow past a quasi-aircraft composed of abody, a sweepback wing and a tail unit in a physical space when the aircraft has nolift. The design condition of the shockless transonic flow is that the Mach numberof the uniform flow is 0.87 and the aircraft angle of attack is zero. The applyingmethod is the extended artificial flow method for a three-dimensional potentialflow and the flow model has effects of walls of a wind tunnel.

• 社団法人日本物理学会の論文
• 1983-08-15

著者

• Nakamura Masayoshi

  National Aerospace Laboratory

関連論文

• Numerical Design of a Shockless Transonic Quasi-Aircraft

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