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Accession Number:
ADA343835
Title:
Large Eddy Simulation of Supersonic Inlet Flows
Descriptive Note:
Final technical rept. 1 Jan 95-30 Sep 97
Corporate Author:
STANFORD UNIV CA DEPT OF MECHANICAL ENGINEERING
Report Date:
1998-04-01
Pagination or Media Count:
82.0
Abstract:
The interaction of a shock wave with a turbulent boundary layer is a central problem in supersonic inlet flows. This work uses numerical and analytical techniques to study shockturbulence interaction in order to identify and explain factors important in shockboundary layer interaction. Direct numerical simulation of a normal shock wave with an isotropic turbulent field of vorticity and entropy fluctuations showed that negative upstream correlation between the vorticity and entropy fluctuations enhances the turbulence across the shock. Positive upstream correlation has a suppressing effect. A new numerical method providing excellent high wavenumber resolution while reducing the computational cost was developed. A model with no adjustable constants was developed to study the vortex breakdown resulting from the interaction of canard or forbody vortices with the shock waves in a supersonic inlet flow. Very good agreement with both experiment and computation was obtained. A numerical method to compute shockturbulence interaction using a conservative form of the Large Eddy Simulation LES equations has been developed and validated. LES of the interaction of isotropic turbulence with a normal shock was performed and comparisons with direct numerical simulation DNS results were favorable. A new Fortran 90 code has been developed for the computation of shockturbulence interaction. The code is an improved version of codes used previously in shockturbulence interaction simulations.
Distribution Statement:
APPROVED FOR PUBLIC RELEASE
