Effects of Wall Cooling and Leading-Edge Blunting on Ramp-Induced, Laminar Flow Separations at Mach Numbers from 3 through 6

Abstract

The effects of wall cooling and nose bluntness on laminar and transitional reattaching flows induced by a 9.5-degree ramp were investigated at Mach numbers from 3 through 6 measuring the longitudinal surface pressure and heat-transfer rate distributions, as well as the flow-field pressures, at several longitudinal stations. Reynolds number based on flat-plate length was varied from 0.25 to 1.0 million. The trend in the change in interaction length with Reynolds number increase indicated laminar reattachment at all test Reynolds numbers at M = 6 and transitional at the two higher Reynolds numbers at M = 3.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1972
Accession Number
AD0738644

Entities

People

  • J. D. Gray
  • R. W. Rhudy

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Boundary Layer
  • Boundary Layer Transition
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Heat Transfer
  • Instrumentation
  • Layers
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Static Pressure
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.