Computation of three dimensional flows about aircraft configurations

DOI10.1016/0045-7930(73)90017-0zbMath0334.76033OpenAlexW2019648254MaRDI QIDQ1229129

K. Appert

Publication date: 1973

Published in: Computers and Fluids (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1016/0045-7930(73)90017-0

Mathematics Subject Classification ID

Applications to the sciences (65Z05) Supersonic flows (76J20)

Related Items

An unstructured, three-dimensional, shock-fitting solver for hypersonic flows ⋮ A novel stabilization method for high-order shock fitting with finite element methods ⋮ Tracking discontinuities in hyperbolic conservation laws with spectral accuracy ⋮ Test problems, coordinate transformations, and technique for nonsteady compressible flow analysis ⋮ Shock interaction computations on unstructured, two-dimensional grids using a shock-fitting technique ⋮ A locally two-dimensional numerical method for calculating three- dimensional supersonic flows ⋮ A Brief History of Shock-Fitting ⋮ Numerical computation of one-dimensional unsteady flow in channels ⋮ Thirty-six years of shock fitting.

Cites Work

• A time-dependent computational method for blunt body flows.
• Inviscid flowfield about a pointed cone at an angle of attack.
• Importance of Boundary Conditions in the Numerical Treatment of Hyperbolic Equations
• Application of a pseudo‐viscous method to the calculation of the steady supersonic flow past a waisted body

This page was built for publication: Computation of three dimensional flows about aircraft configurations