AN ANALYSIS OF THE ACCURACY OF LIQUID-PROPELLANT ROCKET ENGINE PERFORMANCE MEASUREMENTS IN THE PROPULSION ENGINE TEST CELL (J-2A)

Abstract

Measurements obtained during recent testing in the Propulsion Engine Test Cell (J-2A) are analyzed to determine the accuracy of measuring liquid- propellant rocket engine performance. The equipment and calibration techniques used to obtain the data and the statistical methods employed for error analysis are discussed. The results demonstrated that the one standard deviation errors in thrust, chamber pressure, cell pressure, oxidizer flow rate, and fuel flow rate measurements are less than =0.110, =0.198, =0.769, =0,181, and =0.150%, respectively. The accuracy of the primary calculated performance parameters, thrust coefficient, specific impulse, and characteristic velocity, are =0.226, =0.166, and =0.234% (one standard deviation), respectively.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1965
Accession Number
AD0460563

Entities

People

  • C. W. Harper

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Accuracy
  • Air Force
  • Calibration
  • Cells
  • Engines
  • Errors
  • Flow Rate
  • Liquid Propellant Rocket Engines
  • Liquid Propellants
  • Measurement
  • Pressure Measurement
  • Propellants
  • Recording Systems
  • Rocket Engines
  • Specific Gravity
  • Test Facilities

Fields of Study

  • Physics

Readers

  • Rocket Propulsion.
  • Spectroscopy.