Experimental Study of the Supersonic Turbulent Boundary Layer on a Blunted Axisymmetric Body.

Abstract

Surface pressure distributions and turbulent boundary layer velocity profiles have been measured on a tangent-ogive cylinder model at small angles of attack (0-4.5 deg) in a high Reynolds number, Mach 3 airflow. The model wall temperature was approximately adiabatic. The measurements were made using pointed, tangent-hemisphere and flat-faced nose tips. The effects of tip blunting on the wind-and leeside velocity profiles, integral thicknesses, shape factor, power law exponent, skin friction coefficient and wake strength parameter are presented. It is shown that the results obtained using different geometry tips can be correlated using a bluntness length-scale obtained by integration of the local tip surface angle from the stagnation point to the point corresponding to shock detachment.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Sep 30, 1985
Accession Number
ADA163736

Entities

People

  • D. S. Dolling

Organizations

  • University of Texas at Austin

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Bodies
  • Boundary Layer
  • Coefficients
  • Computational Fluid Dynamics
  • Engineering
  • Fluid Dynamics
  • Geometry
  • Mach Number
  • Measurement
  • Nose Tips
  • Pressure Distribution
  • Pressure Gradients
  • Reynolds Number
  • Skin Friction
  • Stagnation Point
  • Three Dimensional
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Boundary Layers
  • Hypersonics - Hypersonic Flow