Effect of spike on steady and unsteady flow over a blunt body at supersonic speed
Author:
Publisher
Elsevier BV
Subject
Aerospace Engineering
Reference45 articles.
1. D.H. Crawford, Investigation of flow over a spiked nose hemisphere-cylinder at Mach number of 6.8, NASA-TN-D-118, Dec. 1959.
2. Numerical simulation of the flow field over conical, disc and flat spiked body at mach 6;Mehta;Aeronaut. J.,2010
3. Navier–Stokes solution for a heat shield with and without a forward facing spike;Mehta;Comput. Fluids,1997
4. Drag reduction for spike attached to blunt-nosed body at Mach 6, Engineering Notes;Kalimuthu;J. Spacecr. Rockets,2010
5. Shock tunnel study of spiked aerodynamic bodies flying at hypersonic mach numbers;Menezes;Shock Waves,2002
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