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Comparison Of Theoretical And Experimental Thrust Performance Of A 10301 Area Ratio Rocket Nozzle At A Chamber Pressure Of 2413 Kn M2 350 Psia
Download Comparison Of Theoretical And Experimental Thrust Performance Of A 10301 Area Ratio Rocket Nozzle At A Chamber Pressure Of 2413 Kn M2 350 Psia full books in PDF, epub, and Kindle. Read online Comparison Of Theoretical And Experimental Thrust Performance Of A 10301 Area Ratio Rocket Nozzle At A Chamber Pressure Of 2413 Kn M2 350 Psia ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781723849435 Total Pages :58 pages Book Rating :4.8/5 (494 download)
Book Synopsis High-Area-Ratio Rocket Nozzle at High Combustion Chamber Pressure: Experimental and Analytical Validation by : National Aeronautics and Space Adm Nasa
Download or read book High-Area-Ratio Rocket Nozzle at High Combustion Chamber Pressure: Experimental and Analytical Validation written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-19 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722219987 Total Pages :24 pages Book Rating :4.2/5 (199 download)
Book Synopsis Experimental Performance of a High-Area-Ratio Rocket Nozzle at High Combustion Chamber Pressure by : National Aeronautics and Space Administration (NASA)
Download or read book Experimental Performance of a High-Area-Ratio Rocket Nozzle at High Combustion Chamber Pressure written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-05 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to determine the thrust coefficient of a high-area-ratio rocket nozzle at combustion chamber pressures of 12.4 to 16.5 MPa (1800 to 2400 psia). A nozzle with a modified Rao contour and an expansion area ratio of 1025:1 was tested with hydrogen and oxygen at altitude conditions. The same nozzle, truncated to an area ratio of 440:1, was also tested. Values of thrust coefficient are presented along with characteristic exhaust velocity efficiencies, nozzle wall temperatures, and overall thruster specific impulse. Jankovsky, Robert S. and Kazaroff, John M. and Pavli, Albert J. Glenn Research Center NAS3-27186; RTOP 506-42-72...
Book Synopsis Experimental Performance of a Hydrogen-fluorine Rocket Engine at Several Chamber Pressures and Exhaust-nozzle Expansion Area Ratios by : William L. Jones
Download or read book Experimental Performance of a Hydrogen-fluorine Rocket Engine at Several Chamber Pressures and Exhaust-nozzle Expansion Area Ratios written by William L. Jones and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Theoretical Performance of Hydrogen-oxygen Rocket Thrust Chambers by : Gilbert K. Sievers
Download or read book Theoretical Performance of Hydrogen-oxygen Rocket Thrust Chambers written by Gilbert K. Sievers and published by . This book was released on 1961 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Fluidic Nozzle Throats in Solid Rocket Motors by : Kan Xie
Download or read book Fluidic Nozzle Throats in Solid Rocket Motors written by Kan Xie and published by Springer. This book was released on 2019-04-26 with total page 241 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book focuses on the performance and application of fluidic nozzle throats for solid rocket motors, discussing their flow details and characterization performance, as well as the influence of the particle phase on their performance. It comprehensively covers a range of fluidic nozzle throats in solid rocket motors and is richly illustrated with impressive figures and full-color photographs. It is a valuable resource for students and researchers in the fields of aeronautics, astronautics and related industries wishing to understand the fundamentals and theories of fluidic nozzle throats and engage in fluidic nozzle throat analysis and design.
Book Synopsis Experimental Investigation of the Feasibility of Ablation-cooling a Rocket Nozzle with Possible Application to Solid-propellant Engines by : Richard R. Cullom
Download or read book Experimental Investigation of the Feasibility of Ablation-cooling a Rocket Nozzle with Possible Application to Solid-propellant Engines written by Richard R. Cullom and published by . This book was released on 1961 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Comparison of Rocket Performance Using Exhaust Diffuser and Conventional Techniques for Altitude Simulation by : Joseph N. Sivo
Download or read book Comparison of Rocket Performance Using Exhaust Diffuser and Conventional Techniques for Altitude Simulation written by Joseph N. Sivo and published by . This book was released on 1959 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Computational Prediction of Isolated Performance of an Axisymmetric Nozzle at Mach Number 0.90 by : John R. Carlson
Download or read book Computational Prediction of Isolated Performance of an Axisymmetric Nozzle at Mach Number 0.90 written by John R. Carlson and published by . This book was released on 1994 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
