Paper Title:
Numerical Simulation of the Supersonic Inlet Flow Field
  Abstract

The 2-D internal steady flow of the scramjet inlet-isolator was numerically simulated by the CFD method. The static pressure contours of the scramjet inlet-isolator under different boundary thickness and different back pressure were given. The numerical simulation results of two kinds of reasons which make the inlet un-start are obtained. One is the boundary layer thickness and another is the high back pressure at the exit of the isolator. When the boundary layer thickness increased, air can not smoothly flow into the inlet isolator and caused inlet un-start. Sameness along with the back pressure rise, have the phenomenon of inlet un-start, too. But the reason of un-start is disaffiliate. In the text analyzed the reasons of un-start phenomenon which from two different perspectives on the problem.

  Info
Periodical
Edited by
Honghua Tan
Pages
2119-2123
DOI
10.4028/www.scientific.net/AMM.29-32.2119
Citation
D. M. Cao, H. Y. Lv, X. Y. Zhang, S. B. Hu, "Numerical Simulation of the Supersonic Inlet Flow Field", Applied Mechanics and Materials, Vols. 29-32, pp. 2119-2123, 2010
Online since
August 2010
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$32.00
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