On the Calculation of Thrust Coefficient.

Abstract

The thrust of a rocket motor is generally calculated from the stagnation pressure, the throat area, and a non-dimensional thrust coefficient dependent upon the nozzle expansion area ratio. A comparison is made between momentum balance and pressure integral methods of calculating the ideal vacuum thrust coefficient, and the results used to examine how corrections should be made for nozzle divergence, skin friction and two-phase flow to obtain the real thrust coefficient of the motor. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1980
Accession Number
ADA099791

Entities

People

  • R. C. Parkinson
  • S. A. Mace

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundary Layer
  • Coefficients
  • Composite Propellants
  • Drag
  • Efficiency
  • Equations
  • Flow
  • Flow Rate
  • Friction
  • Gas Laws
  • Mach Number
  • Mass Flow
  • Pressure Distribution
  • Rocket Engines
  • Skin Friction
  • Stagnation Pressure
  • Two Phase Flow

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.