Assessment of numerical uncertainty around shocks and corners on blunt trailing-edge supercritical airfoils

DOI10.1016/S0045-7930(01)00014-7zbMath0997.76059OpenAlexW2082714828MaRDI QIDQ5948593

Ching-Fang A. Chen, Brian E. Thompson, Robert D. Lotz

Publication date: 10 February 2002

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

Full work available at URL: https://doi.org/10.1016/s0045-7930(01)00014-7

zbMATH Keywords

shockliftpressurecornersgrid refinementaerodynamic dragblunt trailing-edge supercritical airfoilscompressible Reynolds-averaged Navier Stokes equationsgrid convergence index

Mathematics Subject Classification ID

Shock waves and blast waves in fluid mechanics (76L05) Transonic flows (76H05) Finite difference methods applied to problems in fluid mechanics (76M20) General aerodynamics and subsonic flows (76G25)

Related Items (1)

Grid refinement study for three dimensional CFD model involving incompressible free surface flow and rotating object

Uses Software

• Spalart-Allmaras

Cites Work

• On the structure and use of linearized block implicit schemes
• Solution of the multidimensional compressible Navier-Stokes equations by a generalized implicit method
• A flux‐based modified method of characteristics
• Unnamed Item

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