Computation of supersonic inviscid flow around wings with a detached shock wave

DOI10.1016/0045-7825(83)90029-4zbMath0523.76055OpenAlexW1963546961MaRDI QIDQ1056631

G. P. Voskresenskij

Publication date: 1983

Published in: Computer Methods in Applied Mechanics and Engineering (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1016/0045-7825(83)90029-4

zbMATH Keywords

steady Euler equationscontrol partdetached shockelliptic planformfront part of wingprogonka proceduresecond order methodunsteady solution methodwing and shock coordinate surfaceswing-tip

Mathematics Subject Classification ID

Compressible fluids and gas dynamics (76N99) Finite difference methods for boundary value problems involving PDEs (65N06) Supersonic flows (76J20) Jets and cavities, cavitation, free-streamline theory, water-entry problems, airfoil and hydrofoil theory, sloshing (76B10) Basic methods in fluid mechanics (76M99) Numerical solution of discretized equations for boundary value problems involving PDEs (65N22)

Cites Work

• Numerical solution of the problem of unsteady supersonic flow around the front part of the wings with a detached shock wave
• A New Method of Interpolation and Smooth Curve Fitting Based on Local Procedures
• Unnamed Item

This page was built for publication: Computation of supersonic inviscid flow around wings with a detached shock wave