An Experimental Investigation of Supersonic Flow Past Yawed Cones

Abstract

An experimental investigation of supersonic flow around cones was conducted at a free stream mach number of 2.72 and Reynolds number per foot of 1660000. Three cones of semi-apex angles of 10 deg, 15 deg, and 10 deg were investigated at relative incidences up to 3. In addition to measuring surface pressure, a detailed study of the flow in the plane of symmetry phi = 180 deg was made by means of a pitot-hot wire probe. The shape of the outer shock wave as well as of the imbedded shocks were determined. Oil and vapor screen techniques and a Schlieren system were used to visualize the flow field.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1971
Accession Number
AD0728233

Entities

People

  • Rafael Yahalom

Organizations

  • University of California, Berkeley

Tags

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Force
  • Boundary Layer
  • Computational Fluid Dynamics
  • Data Reduction
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Heat Transfer
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Turbulent Mixing
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion Dynamics and Shock Wave Physics.
  • Fluid Dynamics.

Technology Areas

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