NASA STI Repository (National Aeronautics and Space Administration) · 1988 · 63 citations · 4 references
Open access
Numerical AnalysisAeroacousticsEngineeringFluid MechanicsMechanical EngineeringGeometric Singular Perturbation TheoryComputational MechanicsBoundary LayerStabilityUnsteady FlowCompressible FlowNumerical SimulationNumerical StabilitySpectral Collocation SolutionPerturbation MethodMultiphase FlowSupersonic CombustionSingularly Perturbed ProblemAerospace EngineeringTurbulence ModelingSpectral AnalysisAerodynamicsStaggered Pressure MeshShear Flow StabilityStaggered Mesh
A newly developed spectral compressible linear stability code (SPECLS) (staggered pressure mesh) is presented for analysis of shear flow stability, and applied to high speed boundary layers and free shear flows. The formulation utilizes the first application of a staggered mesh for a compressible flow analysis by a spectral technique. An order of magnitude less number of points is needed for equivalent accuracy of growth rates compared to those calculated by a finite difference formulation. Supersonic disturbances which are found to have oscillatory structures were resolved by a spectral multi-domain discretization, which requires a factor of three fewer points than the single domain spectral stability code. It is indicated, as expected, that stability of mixing layers is enhanced by viscosity and increasing Mach number. The mean flow involves a jet being injected into a quiescent gas. Higher temperatures of the injected gas is also found to enhance stability characteristics of the free shear layer.
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