Performance study of a supersonic inlet in the presence of a heat source

Soltani, M. R ; Sharif University of Technology | 2011

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  1. Type of Document: Article
  2. DOI: 10.1016/j.scient.2011.05.027
  3. Publisher: 2011
  4. Abstract:
  5. The flow over a supersonic inlet has been investigated experimentally and numerically at a free stream Mach number of 2 and a zero degree angle of attack. Wind tunnel tests were performed to obtain the performance parameters of the inlet and were used as a baseline and validation tools for the numerical code. A heat source was added to the flow field at a distance ahead of the inlet. The effect of heat source addition on the main performance parameters of the inlet is investigated numerically. Results show that the heat source considerably reduces drag coefficient; however, its effect on pressure recovery is not favorable. This unfavorable effect was then minimized by controlling heat source parameters, such as its location, size and shape. For the optimum condition, drag coefficient reduces considerably, inlet mass flow rate increases, but pressure recovery slightly decreases
  6. Keywords:
  7. Heat source ; Mass flow rate ; Supersonic inlet ; Free stream mach numbers ; Heat sources ; Numerical code ; Optimum conditions ; Performance parameters ; Performance study ; Pressure recovery ; Size and shape ; Supersonic inlets ; Validation tools ; Wind tunnel tests ; Aerodynamics ; Drag ; Drag coefficient ; Flow rate ; Intake systems ; Mach number ; Mass transfer ; Pipe flow ; Pressure effects ; Recovery ; Inlet flow ; Baseline survey ; Flow field ; Model validation ; Numerical model ; Optimization ; Performance assessment ; Wind tunnel
  8. Source: Scientia Iranica ; Volume 18, Issue 3 B , 2011 , Pages 375-382 ; 10263098 (ISSN)
  9. URL: http://www.sciencedirect.com/science/article/pii/S1026309811000927