ADVANCED CRYOGENIC ROCKET ENGINE PROGRAM AEROSPIKE NOZZLE CONCEPT

Abstract

Analysis and preliminary design of an advanced rocket engine using an aerospike nozzle and analysis, test hardware design, and test evaluation of thrust chamber performance and thrust chamber durability are described.

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Document Details

Document Type
Technical Report
Publication Date
Jun 30, 1966
Accession Number
AD0373614

Entities

People

  • Vernon L. Mahugh

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerospike Engines
  • Air Flow
  • Air Force
  • Base Pressure
  • Boundary Layer
  • Combustion
  • Combustion Chambers
  • Fabrication
  • Flow Fields
  • Fluid Dynamics
  • Heat Transfer
  • Heat Transfer Coefficients
  • Ignition
  • Rocket Engines
  • Secondary Flow
  • Test And Evaluation
  • Turbines

Fields of Study

  • Physics

Readers

  • Aerospace Test and Evaluation
  • Rocket Propulsion.