Computational Analysis of 2D Transition Inlets for Supersonic Capture

Abstract

Scramjets are the futuristic propulsion technology for supersonic and hypersonic flights. Transition inlets form one of the major technologies to make the Scramjets more utilizable in reality. This paper deals with the 2-dimensional computational analysis of the supersonic capture of the transition inlets using the finite volume approach of ANSYS. The main objective of this paper is to demonstrate the advantage of the transition inlets over the conventional ramp inlets. This study involves sharp-edged ramp, smooth-edged ramp and transition ramp. Simulation of the inlet at supersonic capture has been done using the SST k-omega turbulence model along with a density-based solver with Roe flux. The performance of the inlet is calculated in terms of the total pressure recovery. Along with this the static pressure, Mach number variation through the inlet and the internal reflected shocks at the isolation chamber are studied. The 2D study of the transition inlet is highly important because the effects of the notch can be studied in depth using the 2D models with minimal number of errors. The comparative study of the 2D transition model helps to validate the advantage of the transition ramps over the conventional ramps. Supersonic capture analysis is inevitable as it determines the starting condition of the inlet. In this paper, the analysis is done for the Mach numbers of 2, 3, and 4.