Boundary Layer Interaction in Hypersonic Air Intake


Authors : Dr. Manoj Veetil, Giri Pallavi.

Volume/Issue : Volume 3 - 2018, Issue 10 - October

Google Scholar : https://goo.gl/DF9R4u

Scribd : https://goo.gl/ES7fcA

Thomson Reuters ResearcherID : https://goo.gl/KTXLC3

The future development in aerospace field will be in hypersonic velocities and consequently hypersonic engines. Since the hypersonic engine is very complicated, design and simulation studies play a vital role in the analysis of flow properties. The main aim of this project was to understand the flow fields for a hypersonic intake. Model analysis using spatial grids were used to understand the effects of parameters which affect the operation of a hypersonic intake, these intakes were strongly influenced by the local grid resolution, and fine grids were generated at the intake section to check different parameters for small region (e.g. Pressure, Mach number, and Temperature). This also helped to reduce spillage and bow shock formation at the tip of cowl intake. Initially an optimum 2-Dimensional (2-D) design was selected, using a trial and error method. 3-Dimensional (3-D) hypersonic intakes were then designed using the final 2-D design dimensions. With the help of gas dynamics, isentropic and geometrical relations, different parameters were calculated. The calculated parameters were compared with the results obtained from the analysis. For designing and meshing, ICEM-CFD was used and numerical simulations were carried out in ANSYS-FLUENT.

Keywords : Hypersonic flow, Grid generation, Cowl intake, spillage, shock formation, Boundary Layer.

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