On the Calculation of Thrust Coefficient.

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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

Author(s):
Parkinson, R. C. ; Mace, S. A.
Author Organization(s):
PROPELLANTS EXPLOSIVES AND ROCKET MOTOR ESTABLISHMENT WESTCOTT (ENGLAND)
Descriptive Note:
Memorandum rept.,
Pagination:
0018

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
PERME-MEMO-150, DRIC-BR-77714
Monitor Series:
BR-77714
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means; JCA_1.3_Human Capital Management; JCA_1_Force Support; JCA_5.3_Planning; JCA_5_Command and Control
Communities of Interest:
Weapons Technologies
Descriptor(s):
*MATHEMATICAL MODELS, *COEFFICIENTS, *ROCKET ENGINES, *THRUST, *TWO PHASE FLOW, VACUUM, BALANCE, EXPANSION, MACH NUMBER, SKIN FRICTION, MOMENTUM, STAGNATION PRESSURE, GAS FLOW, TRANSONIC CHARACTERISTICS, NOZZLE AREA RATIO, UNITED KINGDOM
Field(s)/Group(s):
Numerical Mathematics, Fluid Mechanics, Rocket Engines
Report Date:
1980 Nov 01