LOCAL FLOW CONDITIONS RECOVERY FACTORS AND HEAT-TRANSFER COEFFICIENTS ON THE NOSE OF A HEMISPHERE-CYLINDER AT A MACH NUMBER OF 2.8

Abstract

Local flow conditions, recovery factors, and heat-transfer coefficients were determined experimentally on the hemispheric nose of a hemisphere-cylinder with a laminar boundary layer at M=2.8. Results indicated that the recovery factor may be expressed by the square root of the Prandtl number even in the presence of a pressure gradient. An analysis of the supersonic heat-transfer data revealed that the supersonic values obey a law almost identical to that derived from incompressible theory.

Document Details

Document Type
Technical Report
Publication Date
May 05, 1953
Accession Number
AD0018797

Entities

People

  • Irving Korobkin

Organizations

  • Naval Ordnance Laboratory

Tags

DTIC Thesaurus Topics

  • Boundary Layer
  • Coefficients
  • Heat Transfer
  • Heat Transfer Coefficients
  • Hemispheres
  • Laminar Boundary Layer
  • Layers
  • Mach Number
  • Numbers
  • Prandtl Number
  • Pressure Gradients
  • Recovery
  • Square Roots

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

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