HEAT TRANSFER TO A CONE SEGMENT MODEL,

Abstract

The laminar heat transfer to a portion of a 35 degrees half-angle conical surface has been measured at several angles of attack in a rocket wind tunnel. The free stream Mach number was approximately 7, the pressure altitude was about 100,000 ft and the free stream Reynolds number was about 500,000 per foot. The heat transfer along the model centerline was in reasonable agreement with that predicted by conical flow theory. The surface heat transfer near the leading edges was not more than 35% greater than that at the centerline at 20 degrees angle of attack and not more than 10 to 15% greater at 50 degrees angle of attack. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jul 26, 1960
Accession Number
AD0682122

Entities

People

  • M. L. Streiff

Organizations

  • General Dynamics

Tags

DTIC Thesaurus Topics

  • Agreements
  • Altitude
  • Flow
  • Free Stream
  • Heat Transfer
  • Leading Edges
  • Mach Number
  • Reynolds Number
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Mechanics and Fluid Dynamics.