INVESTIGATION OF HYPERSONIC FLOW OVER BLUNTED PLATES AND CONE

Abstract

Heat transfer rates and pressure distributions on three basic shapes were investigated at a nominal Mach number of 8 and free-stream Reynolds numbers from 0.43 to 3.4 million per foot. The models were a 0.4-in. nose radius, spherically blunted, 15-deg half-angle cone; two flat plate models with 0. 10-in. and 0. 50-in. cylindrical blunting; and a modified leading-edge plate with auxiliary planes to produce changing body shape within the elliptic flow region. The tests produced data showing the effect on heat transfer rates of the interaction of the essentially inviscid, rotational flow behind the bow shock with the viscous boundary layer on the body. The results of pressure distribution tests show good agreement with theory. Heat transfer rates over the entire body were accurately predicted through the use of outer-edge boundary-layer conditions obtained from isentropic expansion from normal-shock stagnation conditions.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
May 01, 1960
Accession Number
AD0221626

Entities

People

  • J. O. Rippey
  • J. P. Rhudy
  • R. S. Hiers

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Bow Shock
  • Data Reduction
  • Flat Plate Models
  • Flow
  • Free Stream
  • Heat Transfer
  • Heat Transfer Coefficients
  • Instrumentation
  • Layers
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Pressure Measurement
  • Stagnation Pressure
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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