Numerical Simulation of Flow through Scramjet Inlet - Isolator Model with Pressure Feedback Yuvraj Sarout, R Thundil Karuppa Raj and Senthilkumar P* School of Mechanical Engineering, Vellore Institute of Technology, Vellore,Tamil Nadu, India * Corresponding author psk@vit.ac.in ABSTRACT This paper states significant points about the performance enhancement of supersonic air intake model through the implementation of pressure feedback system with different connecting locations. A Mach 5, supersonic air intake model with a larger shoulder separation and other two separations at cowl lip and inside the isolator is studied. This model has been simulated using CFD package Ansys Fluent-18. A Comparison of numerical simulation and experimental measurements is presented to validate the correctness and accuracy of numerical frame work followed in the current study. Suitably refined mesh with higher order spatial accuracy of the solver aided in accurate capturing of the flow field. Three different pressure feedback configurations were investigated to study the performance improvement of the intake system. Improvement in total pressure at the outlet of isolator is accomplished through the use of pressure feedback system by reducing the separation bubble to a great extent. From the study, it is found that the flow through the pressure feedback system happens due to the pressure difference between the separation bubble and the upstream side regular flow. This pressure feedback system can reduce the intensity of shock wave boundary layer interaction and the size of the bubble occurring at the isolator entry section, cowl lip and inside upper part of isolator. Increment in total pressure recovery depicts the better performance due to the implementation of pressure feedback system. This study demonstrates the scope of overall improvement in scramjet engine performance through the use of pressure feedback system NOMENCLATURE p static pressure x Distance along flow direction Ht Throat height L Total length of Ramp p∞ Free Stream Pressure Downloaded by UNIVERSITY OF TORONTO on January 8, 2020 | http://arc.aiaa.org | DOI: 10.2514/6.2020-0650 AIAA Scitech 2020 Forum 6-10 January 2020, Orlando, FL 10.2514/6.2020-0650 Copyright © 2020 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. AIAA SciTech Forum