A Performance Comparison of Two Small Rocket Nozzles PDF Download
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Author: Lynn A. Arrington
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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Author: Lynn A. Arrington
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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Book Description
Author: Lynn A. Arrington
Publisher:
ISBN:
Category : Reynolds number
Languages : en
Pages : 11
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Author: K. J. Davidian
Publisher:
ISBN:
Category :
Languages : en
Pages : 10
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Author: Arnold T. Stokes
Publisher:
ISBN:
Category :
Languages : en
Pages : 46
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Book Description
The report presents performance data for double-cornered plug nozzles for comparison with convergent-divergent nozzles. A conventional convergent- divergent (C-D) nozzle was used to develop the propellant charge, ignition and ballistics, and as a baseline for plug nozzle performance evaluation. (Author).
Author: Tamara A. Smith
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 28
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Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 740
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Author: Michael Matthew Micci
Publisher: AIAA
ISBN: 9781600864391
Category : Microspacecraft
Languages : en
Pages : 520
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Author: Franklin P. Durham
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 62
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781723849435
Category : Science
Languages : en
Pages : 58
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Book Description
Experimental data were obtained on an optimally contoured nozzle with an area ratio of 1025:1 and on a truncated version of this nozzle with an area ratio of 440:1. The nozzles were tested with gaseous hydrogen and liquid oxygen propellants at combustion chamber pressures of 1800 to 2400 psia and mixture ratios of 3.89 to 6.15. This report compares the experimental performance, heat transfer, and boundary layer total pressure measurements with theoretical predictions of the current Joint Army, Navy, NASA, Air Force (JANNAF) developed methodology. This methodology makes use of the Two-Dimensional Kinetics (TDK) nozzle performance code. Comparisons of the TDK-predicted performance to experimentally attained thrust performance indicated that both the vacuum thrust coefficient and the vacuum specific impulse values were approximately 2.0-percent higher than the turbulent prediction for the 1025:1 configurations, and approximately 0.25-percent higher than the turbulent prediction for the 440:1 configuration. Nozzle wall temperatures were measured on the outside of a thin-walled heat sink nozzle during the test fittings. Nozzle heat fluxes were calculated front the time histories of these temperatures and compared with predictions made with the TDK code. The heat flux values were overpredicted for all cases. The results range from nearly 100 percent at an area ratio of 50 to only approximately 3 percent at an area ratio of 975. Values of the integral of the heat flux as a function of nozzle surface area were also calculated. Comparisons of the experiment with analyses of the heat flux and the heat rate per axial length also show that the experimental values were lower than the predicted value. Three boundary layer rakes mounted on the nozzle exit were used for boundary layer measurements. This arrangement allowed total pressure measurements to be obtained at 14 different distances from the nozzle wall. A comparison of boundary layer total pressure profiles and analytical
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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