Investigation of Corner Rounding Effects on the Performance of a Supersonic Air Intake

In this research, flow is simulated numerically through and around a mixed-compression intake to investigate effects of corner rounding on intake performance at free stream Mach numbers of 1.8, 2 and 2.2 and atzero degrees angle of attack. Furthermore, effects of different Mach numbers and back pressures are studied. Total Pressure Recovery TPR Flow Distortion FD Mass Flow Ratio MFR and dragcoefficient CD are chosen as the intake performanceparameters. CFD results are validated with experimental data. Results showed that increment of back pressure generally can improve the performancewhile increasing Mach number has unfavorable effectson TPR. Also applying fillet can significantly improve performance parameters FD of and MFR . However it doesn‟t TPR and CD .

کلیدواژه ها:

Supersonic intake ، Intake performance ، fillet radius of curvature ، Mach number