Commenced in January 2007
Paper Count: 30174
Effects of Mach Number and Angle of Attack on Mass Flow Rates and Entropy Gain in a Supersonic Inlet
Abstract:A parametric study of a mixed-compression supersonic inlet is performed and reported. The effects of inlet Mach Numbers, varying from 4 to 10, and angle of attack, varying from 0 to 10, are reported for a constant inlet dynamic pressure. The paper looked at the variations of mass flow rates through the inlet, gain in entropy through the inlet, and the angles of the external oblique shocks. The mass flow rates were found to decrease monotonically with Mach numbers and increase with angle of attacks. On the other hand the entropy gain through the inlet increased with increasing Mach number and angle of attack. The variation in static pressure was found to be identical from the inlet throat to the exit for Mach number values higher than 6.
Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1080672Procedia APA BibTeX Chicago EndNote Harvard JSON MLA RIS XML ISO 690 PDF Downloads 2270
 D. Rozario and Z. Zouaoui, "Computational Fluid Dynamic Analysis of Scramjet Inlet", University of Wales, UK
 Two-Dimensional Bifurcated Inlet/Engine Tests Completed in 10- by 10- Foot Supersonic Wind Tunnel. Research and Technology 1998. NASA TMÔÇö1999-208815, 1999, p. 107.
 S. Emami, C.A. Trexler, A.H. Auslender and J. P. Weinder "Experimental Investigation of Inlet-Combustor Isolators for a Dual- Mode Scramjet at a Mach number of 4", NASA Technical Paper 3502, May 1995.
 M. Kumar and S Mittal "Euler Flow in a Supersonic Mixed- Compression Inlet", International Journal for Numerical Methods in Fluids, 2006; 50: 1405 - 1423.
 E.A. Luke "CHEM: Computational Combustion Modeling", Mississippi State University, 2004.