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Effects of boundary-layer bleed parameters on supersonic intake performance

Soltani, M. R ; Sharif University of Technology | 2015

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  1. Type of Document: Article
  2. DOI: 10.2514/1.B35461
  3. Publisher: American Institute of Aeronautics and Astronautics Inc , 2015
  4. Abstract:
  5. The performance and the buzz onset of a supersonic mixed-compression axisymmetric intake are experimentally investigated. Effectsof the slot bleed position, angle, and width onthe intake performance and onthe buzz initiation at three different Mach numbers of 1.8, 2.0, and 2.2 and at a zero degree angle of attack are studied. The intake performance is assessed using the total pressure recovery, mass flow ratio, flow distortion, and bleed mass flow ratio. The results show that applying the bleed at a position near the intake entrance and reducing the bleed entrance slant angle and width all improve the intake performance considerably. Moreover, these parameters postpone the buzz onset. In addition, it is found that the vertical position of the intersection point of the barrier and normal shocks plays an important role in the intake pressure recovery
  6. Keywords:
  7. Aerodynamics ; Angle of attack ; Mass transfer ; Bleed mass flows ; Intake pressure ; Intersection points ; Mass flow ratios ; Mixed compressions ; Supersonic intake ; Total pressure recovery ; Vertical positions ; Boundary layers
  8. Source: Journal of Propulsion and Power ; Volume 31, Issue 3 , March , 2015 , Pages 826-836 ; 07484658 (ISSN)
  9. URL: http://arc.aiaa.org/doi/10.2514/1.B35461