SHOCKWAVE BOUNDARY LAYER INTERACTION AT VARIOUS MACH NUMBERS AND ANGLES OF ATTACKS

Abstract

This research examines the shockwave characteristics at a double ramp inlet and its performances at different angles of attacks (AoAs) with various Mach numbers. The k-omega (k–ω) shear stress transport (SST) turbulence model was used over a two-dimensional double ramp inlet at free-stream Mach numbers of 4, 5 and 6 with various AoAs in the range of -10 to 10°. The experimental data was used to validate the numerical results. Analysis of the internal shock structures showed that at a Mach number lower or greater than the intended Mach number, the shock waves’ impact on the cowl inlet was considerably influenced. Moreover, the Mach number and AoA had major impact on overall pressure, kinetic energy and compression process efficiencies, whereby kinetic energy and compression process efficiencies improve when AoA is increased. An increase in AoA also shifts the shock wave inside the isolator, while decrease in AoA expels the shockwave from the isolator at the design Mach number. It can be concluded that the interaction of the shockwave with the cowl would be affected by various AoAs.
Keywords: Shockwave boundary layer interaction (SWBLI); supersonic; hypersonic; angle of attack (AoA); flow control.

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