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Investigation of Hypersonic Inlet Shock-Wave Boundary Layer Interaction. Part II. Continuous Flow Test and Analyses.


AD636981

Publication Date 1966
Personal Author Kutschenreuter, P. H.; Brown, D. L.; Hoelmer, W.
Page Count 2
Abstract The computational procedure developed in Phase I for estimating laminar boundary layer properties through impinging shock induced laminar boundary layer interactions was modified to account for entropy change of the inviscid streamlines in that isentropic assumptions were used in the initial formulation. Perturbation studies on the effects of wall shear on interaction length have identified the importance of the profile shape factor in such calculations. A Users' Manual for the laminar computational program is contained. Three incident shock models were designed for use in the experimental program conducted in the Ames 3.5 Foot Hypersonic Tunnel. Aided by analysis of the experimental data, a simplified flow model was formulated for the case of a two-dimensional turbulent boundary layer incident shock interaction. (Author)
Keywords
  • Duct inlets
  • Hypersonic flow
  • Boundary layer
  • Shock waves
  • Tests
  • Analysis
  • Flow separation
  • Models(Simulations)
  • Turbulence
  • Laminar boundary layer
NTIS Subject Category
  • 46B - Fluid Mechanics
Corporate Authors General Electric C Evendale Ohio Advanced Technology and Demonstrator Programs Dept
Document Type Technical Report
Title Note Rept. for Jul 63-Apr 66.
NTIS Issue Number 196618
Contract Number
  • AF 33(657)-11747
Investigation of Hypersonic Inlet Shock-Wave Boundary Layer Interaction. Part II. Continuous Flow Test and Analyses.
Investigation of Hypersonic Inlet Shock-Wave Boundary Layer Interaction. Part II. Continuous Flow Test and Analyses.
AD636981

  • Duct inlets
  • Hypersonic flow
  • Boundary layer
  • Shock waves
  • Tests
  • Analysis
  • Flow separation
  • Models(Simulations)
  • Turbulence
  • Laminar boundary layer
  • 46B - Fluid Mechanics
  • AF 33(657)-11747
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