EVALUATION OF SHORT-DURATION ROCKET ENGINE TECHNIQUE FOR BASE HEAT TESTING WITH EXTERNAL AIRFLOW

Abstract

Base recirculation data were obtained on a 5.47-%-scale model of the Saturn 1-Block 2 booster at trajectory Mach numbers of 1.16 and 1.63. The rocket nozzle flow was produced by use of the short-duration combustor. The turbine exhaust gases were simulated by hydrogen. The test objectives were (1) to compare results obtained by the short-duration technique to those obtained by long-duration test methods and (2) to evaluate the operational advantages of the short-duration method as compared to other techniques. A comparison of model test to flight test data is also presented.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1966
Accession Number
AD0485277

Entities

People

  • John G. Dawson Jr.

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Sensors
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundary Layer
  • Calorific Value
  • Combustion
  • Combustion Chambers
  • Combustors
  • Exhaust Gases
  • Heat Transfer
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Recording Systems
  • Steady Flow
  • Steady State
  • Test And Evaluation
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Aerospace Test and Evaluation
  • Combustion and Flow Dynamics.
  • Rocket Propulsion.