Computation of unsteady shock-induced vortex separation

Shigeru Obayashi, Kunio Kuwahara, Hirotoshi Kubota

Research output: Contribution to conferencePaper

Abstract

Transonic flows around an NACA0012 airfoil were simulated by directly solving the full Navier-Stokes equations without any turbulence model. The implicit LU factored scheme was used with improved accuracy. The results of unsteady computations without any turbulence model show the clear dependence of the flow on the Reynolds number, and agree qualitatively with experimental observatiogs well even at Reynolds numbers over 10. Unsteady shock-induced vortex separation was observed at all the Reynolds numbers. To check the results against experiment, the improved scheme was coupled with the Baldwin-Lomax turbulence model obtaining excellent agreement with experiment.

Original languageEnglish
Publication statusPublished - 1985 Jan 1
Externally publishedYes
EventAlAA 23rd Aerospace Sciences Meeting, 1985 - Reno, United States
Duration: 1985 Jan 141985 Jan 17

Other

OtherAlAA 23rd Aerospace Sciences Meeting, 1985
CountryUnited States
CityReno
Period85/1/1485/1/17

ASJC Scopus subject areas

  • Aerospace Engineering

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    Obayashi, S., Kuwahara, K., & Kubota, H. (1985). Computation of unsteady shock-induced vortex separation. Paper presented at AlAA 23rd Aerospace Sciences Meeting, 1985, Reno, United States.