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Performance investigation of a supersonic air intake in presence of boundary-layer bleed

Soltani, M. R ; Sharif University of Technology

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  1. Type of Document: Article
  2. Abstract:
  3. The performance of an axisymmetric supersonic mixed-compression air intake has been investigated experimentally. The intake has been designed for free stream Mach number of 2.0. This study has two main goals, firstly to investigate the performance of the intake without boundary-layer bleed in design and off-design conditions and secondly to study the effects of a slot bleed on the intake performance. The intake has been tested at free stream Mach numbers of 1.8, 2.0, and 2.2 and zero degree angle of attack. Total pressure recovery (TPR), mass flow ratio (MFR) and flow distortion (FD) have been selected parameters to assess the intake performance. The bleed slot is located upstream of the intake throat and is perpendicular to the compression ramp surface. The suction is done by the naturala pressure difference at the entrance and exit planes of the bleed duct. Results show that applying the boundary-layer suction upstream of the intake throat can considerably improve the intake performance in design and off-design conditions while it does not decrease the intake mass flow rate
  4. Keywords:
  5. Air intakes ; Boundary layers ; Design ; Compression ramps ; Flow distortion ; Free stream mach numbers ; Intake mass flow ; Mass flow ratios ; Off design condition ; Pressure differences ; Total pressure recovery ; Aerodynamics
  6. Source: 32nd AIAA Applied Aerodynamics Conference ; June , 2014
  7. URL: http://pig.sagepub.com/content/early/2014/10/22/0954410014554815