JET IMPINGEMENT HEATING RATES TO A PROPOSED VERNIER FLAME DEFLECTOR,

Abstract

The location of the Atlas vernier engines forward of the main engine compartment presents a problem due to the impingement of the expanded vernier exhaust jet at high altitudes. One of the proposed solutions to this problem is a shield mounted on the missile structure to deflect the jet and prevent impingement. The object of the study was to determine the heat transfer rates to a 1/10 scale model of a proposed 'flame deflector.' Results of tests up to 170,000 feet indicate that heating rates to the proposed deflector at altitudes above 40,000 feet will not vary with the ambient pressure. Heating rates of the order of 1,000,000 BTU/hr-sq ft may be expected to portions of the deflector near the rocket nozzle exit. The results indicate that these heating rates decrease exponentially with distance downstream of the nozzle exit. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 08, 1958
Accession Number
AD0830205

Entities

People

  • R. E. Cruse

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Altitude
  • Deflectors
  • Flame Deflectors
  • Gas Turbine Nozzles
  • Heat Transfer
  • High Altitude
  • Models
  • Nozzles
  • Rocket Nozzles
  • Rockets
  • Scale Models

Readers

  • Combustion and Flow Dynamics.