1Institute of Technology, Guru Ghasidas University, Department of Mechanical, Koni, Bilaspur, 495009, India
2Institute of Technology, Guru Ghasidas University, Department of IPE, Koni, Bilaspur, 495009, India
3Christian College of Engineering and Technology, Department of Mechanical, Bhilai, 490026
4Institute of Technology, Guru Ghasidas Vishwavidyalaya, Department of Mechanical Engineering, Koni, Bilaspur, Chhattisgarh, 495009, India
Online published on 25 December, 2015.
The Navier-Stokes equations which govern the counterflow injection cooling at hypersonic speeds along with species continuity equations are solved numerically using CFD. The flowfield variables over a blunt cone are computed at a flow Mach number of 8.0 with helium and air as coolant gases. Analysis has been carried out for an axisymmetric 600 angle blunt module with and without injection cooling since Mach number of 8.0. The numerical result has been successfully validated using standard experimental results for counter flow injection. The numerical data shows about 15%-40% reduction in drag force coefficient for different jet pressures with Air and He injection. Helium gas is found to be a relatively more effective coolant in the counterflow injection cooling.
Hypersonic flow, Aerodynamics wave drag, CFD
