Optimal-contour design for a plane hypersonic engine output unit with account for the boundary layer, length, outer flow, and base end effects

DOI10.1007/BF02698132zbMath0967.76584MaRDI QIDQ5931008

R. K. Tagirov, M. K. Aukin

Publication date: 27 August 2001

Published in: Fluid Dynamics (Search for Journal in Brave)

Mathematics Subject Classification ID

Hypersonic flows (76K05) Flow control and optimization for compressible fluids and gas dynamics (76N25)

Related Items (1)

Features of internal and external flows in high-speed vehicles with a magnetohydrodynamic air-intake

Cites Work

• Determination of the optimal contour of a supersonic jet engine outlet by the direct method
• Necessity of an end face for an optimum two-dimensional afterbody with a boundary layer
• Calculation of the base pressure and enthalpy downstream of a plane or axisymmetric step in supersonic flow with allowance for the effect of the initial boundary layer
• A second-order finite-difference scheme for computing three-dimensional supersonic flows of an ideal gas

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