Effect of Shock Impingement on Heat Transfer. Part III. An Investigation of Adiabatic Laminar Boundary Layer/Shock Wave Interactions on Curved Walls.

Abstract

Static pressure distributions in supersonic flow have been measured on the surface of a flat plate/curved ramp model and on a flat plate curved afterbody model with equivalent impinging shock. Under adiabatic supersonic flow conditions, an equivalence between the two configurations is shown to exist. Using this concept of equivalence the Lees-Reeves-Klineberg integral method has been successfully modified to include surface curvature and the predicted static pressure distributions compared directly with the experimental curved ramp data.

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1975
Accession Number
ADA015913

Entities

People

  • David S. Dolling
  • Jean J. Ginoux

Organizations

  • von Kármán Institute for Fluid Dynamics

Tags

DTIC Thesaurus Topics

  • Boundary Layer
  • Curvature
  • Flow
  • Heat Transfer
  • Laminar Boundary Layer
  • Layers
  • Pressure Distribution
  • Shock
  • Shock Waves
  • Static Pressure
  • Supersonic Flow

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Mathematical Modeling and Probability Theory.

Technology Areas

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