Design and Numerical Analysis of Diverter-less Supersonic Inlet with various Three-dimensional Bumps
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Abstract
Diverter-less supersonic inlet for a fighter aircraft requires the 3D bump to give an appropriate shock structure along with boundary layer diversion. In this study, different bump surfaces are created using MATLAB program. These bumps are integrated into the intakes and numerical investigations are carried out using ANSYS Fluent software for supersonic flow regimes (M = 1.2 to 2). The four intakes, namely clean intake, mod1 bump intake, mod2 bump intake and mod3 bump intake are modelled and comparative investigations are performed. The investigation shows the ability of diverter-less supersonic inlet to achieve improved total pressure recovery and boundary layer interaction at supersonic conditions. Among all the configurations, mod3 bump intake viz., intake integrated with original bump gives a better pressure recovery as well as reduction of the inlet duct Mach number.
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