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Numerical Simulation and Parametric Study of a Supersonic Intake
Year: 2013
Abstract:
was undertaken using the designed base case at a constant Mach number of 2 and at 0° angle of attack. The effects of various important parameters such as free stream Mach number, spike deflection angle, and back pressure ratio on the total pressure recovery, mass...
Performance Investigation of a Supersonic Air Intake in the Presence of the Boundary Layer Suction
Year: 2014
Abstract:
.2 and at zero degrees angle of attack. Total pressure recovery, mass flow ratio, and flow distortion have been selected to assess the intake performance. The bleed slot is located upstream of the intake throat
perpendicular to the compression ramp surface...