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Effects of bleed position on the stability of a supersonic inlet

Soltani, M. R ; Sharif University of Technology | 2016

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  1. Type of Document: Article
  2. DOI: 10.2514/1.B36162
  3. Publisher: American Institute of Aeronautics and Astronautics Inc , 2016
  4. Abstract:
  5. Effects of various boundary-layer bleed locations on the stability of an axisymmetric supersonic inlet has been investigated experimentally. The bleeds were located on the inlet compression cone and were designed to improve the stability margin of the inlet. The main objective of the study was to identify the boundary-layer bleed location and its effectsonthe improvementofthestability marginofthe inlet.Inaddition,a buzz precursordetection methodology based on the rms level has been introduced. Experiments have been carried out on a mixed-compression inlet with a design Mach number of 2.0 and three different bleed locations at three freestream Mach numbers of 1.8, 2.0, and 2.2. All tests were conducted at an angle of attack of0 deg. The results show that, based on the individual design of aninlet, alocation can be found that the spilled normal shock stands at this location and consequently separation starts at the buzz onset. If the bleed slot is located in this place, the subcritical performance and stability margin of the inlet can be enhanced
  6. Keywords:
  7. Aerodynamics ; Angle of attack ; Boundary layers ; Intake systems ; Location ; Mach number ; Axisymmetric ; Freestream mach number ; Mixed compressions ; Stability margins ; Supersonic inlets ; Stability
  8. Source: Journal of Propulsion and Power ; Volume 32, Issue 5 , 2016 , Pages 1153-1166 ; 07484658 (ISSN)
  9. URL: https://arc.aiaa.org/doi/10.2514/1.B36162