Experimental Study of the Hypersonic Flow Over Convex Conic Model Resembling the Nosetip of a Reentry Vehicle.

Abstract

Heat transfer and pressure measurements have been measured on a convex conic configuration with a spherical nosetip in the von Karman Institute Longshot free pison tunnel at M=15 and 20. The test flow parameters achieved closely simulated reentry aerodynamic conditions. Information derived from the measurements and also from schlieren photographs enabled statements to be made on the effect of Mach number, Re number, surface roughness and flow incidence on the flow over the model. (Author)

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1978
Accession Number
ADA053734

Entities

People

  • Bryan E. Richards

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

Communities of Interest

  • Air Platforms
  • Sensors
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Flow
  • Flow Fields
  • Fluid Dynamics
  • Heat Transfer
  • Hypersonic Flow
  • Mach Number
  • Measurement
  • Photographs
  • Photography
  • Pressure Distribution
  • Pressure Measurement
  • Reentry Vehicles
  • Reynolds Number
  • Roughness
  • Surface Roughness
  • Surface Temperature

Fields of Study

  • Physics

Readers

  • Computer Science.
  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

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