Effect of density gradients in confined supersonic shear layers, part 1
Abstract
The effect of density gradients on the supersonic wall modes (acoustic modes) of a 2D confined compressible shear layer were investigated using linear analysis. Due to the inadequacies of the hyperbolic tangent profile, the boundary layer basic profiles were used. First a test case was taken with the same parameters as in Tam and Hu's analysis with convective Mach number M(sub c) = 1.836 and density ratio of 1.398. Three generalized inflection points were found giving rise to three modes. The first two show similar properties to the Class A and B modes, and the third is an 'inner mode' which will be called a Class C mode. As the density ratio is increased, the smallest of the three neutral phase speeds tends towards the speed of the lower velocity stream, and the other two eventually coalesce and then disappear. These two effects lead to a linear resonance between the Class B modes which increases the cutoff frequency and growth rate of the lowest mode. In fact, growth rates of 24 times the test case were found as the density ratio was increased to 7. A similar trend is observed for the Class A modes when the density ratio is decreased from the test case, but the growth rate is not changed by much from the test case.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 November 1994
 Bibcode:
 1994STIN...9524412P
 Keywords:

 Acoustic Properties;
 Combustion Chambers;
 Compressible Flow;
 Density (Mass/Volume);
 Euler Equations Of Motion;
 Mathematical Models;
 Shear Layers;
 Supersonic Combustion;
 Supersonic Speed;
 Boundary Layers;
 Flow Stability;
 Frequencies;
 Mach Number;
 Resonance;
 Fluid Mechanics and Heat Transfer