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Download or read book The Prediction of Nozzle Performance and Heat Transfer in Hydrogen/Oxygen Rocket Engine, (NASA-TM-106617), May 1994 written by and published by . This book was released on with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Kenneth J. Kacynski
Publisher :
ISBN 13 :
Total Pages : 16 pages
Book Rating : 4.:/5 (317 download)
Download or read book The Prediction of Nozzle Performance and Heat Transfer in Hydrogen/oxygen Rocket Engines with Transpiration Cooling, Film Cooling, and High Area Ratios written by Kenneth J. Kacynski and published by . This book was released on 1994 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 652 pages
Book Rating : 4.:/5 (319 download)
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 652 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : John R. Howell
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (317 download)
Download or read book Analysis of Heat-transfer Effects in Rocket Nozzles Operating with Very High-temperature Hydrogen written by John R. Howell and published by . This book was released on 1965 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical technique suitable for & the solution of complex energy transfer problems involving coupled radiant and convective energy transfer is developed. Solutions for the coupled axial wall energy flax distribution in rocket nozzles using hydrogen as a propellant are presented. Flow rates and temperatures studied are near those forecast for gaseous-core nuclear-propulsion systems. Parameters varied are nozzle shape, inlet propellant temperature, mean reactor cavity temperature, and nozzle wall temperature level. The effects of variation of the propellant radiation absorption coefficient with pressure, temperature, and wavelength are presented, and real property variations are used where they appear to be significant. Comparison is made to a simplified, coupled solution using a modified second-order one-dimensional diffusion equation for the radiative transfer. At the temperature levels assumed, radiative transfer may account for a greater portion of the total energy transfer over important portions of the nozzle, and its effects cannot, therefore, be neglected. Extreme energy flaxes (near 3XlO to the 8 Btu/(hr)(sq ft)) are observed for certain cases, and this implies that new nozzle cooling techniques must be developed.
Author : Gilbert K. Sievers
Publisher :
ISBN 13 :
Total Pages : 88 pages
Book Rating : 4.:/5 (317 download)
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 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: Theoretical rocket performance data for the propellant combination of liquid hydrogen and liquid oxygen are presented in convenient graphical forms to permit rapid determination of specific impulse, vacuum specific impulse, and characteristic velocity. Data are presented for both frozen and equilibrium composition during expansion for chamber pressures of 15, 30, 60, 150, 300, 600, 900 and 1200 pounds per square inch absolute over a wide range of percent fuel from approximately 8 to 34 and area ratios to approximately 300. For rapid calculation of the theoretical nozzle performance with over- or under- expansion, separated flow, and introduction of propellants at different initial conditions or heat loss from the combustion chamber, the following theoretical data are also presented: combustion-chamber temperature, nozzle-exit temperature, and the ratio of chamber-pressure to nozzle-exit pressure. An easy method is given for estimating theoretical specific impulse at chamber pressures other than those presented.
Author :
Publisher :
ISBN 13 :
Total Pages : 552 pages
Book Rating : 4.0/5 ( download)
Download or read book 30th AIAA/ASME/SAE/ASEE Joint Propulsion Conference written by and published by . This book was released on 1994 with total page 552 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781720572084
Total Pages : 56 pages
Book Rating : 4.5/5 (72 download)
Download or read book 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 2018-06 with total page 56 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 : Robert W. Graham
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (31 download)
Download or read book The Use of Energy Thickness in Prediction of Throat Heat Transfer in Rocket Nozzles written by Robert W. Graham and published by . This book was released on 1969 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Energy thickness in prediction of throat heat transfer in rocket nozzles using nozzle geometries and temperature ratios.
Author :
Publisher :
ISBN 13 :
Total Pages : 1028 pages
Book Rating : 4.3/5 (91 download)
Download or read book Government Reports Announcements & Index written by and published by . This book was released on 1994 with total page 1028 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Curt H. Liebert
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (317 download)
Download or read book Application of Various Techniques for Determining Local Heat-transfer Coefficients in a Rocket Engine from Transient Experimental Data written by Curt H. Liebert and published by . This book was released on 1960 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Ralph L. Schacht
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (31 download)
Download or read book Axial and Circumferential Variations of Hot-gas-side Heat-transfer Rates in a Hydrogen-oxygen Rocket written by Ralph L. Schacht and published by . This book was released on 1971 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : John R. Howell
Publisher :
ISBN 13 :
Total Pages : 42 pages
Book Rating : 4.:/5 (31 download)
Download or read book Analysis of Heat-transfer Effects in Rocket Nozzles Operating with Very High-temperature Hydrogen written by John R. Howell and published by . This book was released on 1965 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical technique suitable for& the solution of complex energy transfer problems involving coupled radiant and convective energy transfer is developed. Solutions for the coupled axial wall energy flax distribution in rocket nozzles using hydrogen as a propellant are presented. Flow rates and temperatures studied are near those forecast for gaseous-core nuclear-propulsion systems. Parameters varied are nozzle shape, inlet propellant temperature, mean reactor cavity temperature, and nozzle wall temperature level. The effects of variation of the propellant radiation absorption coefficient with pressure, temperature, and wavelength are presented, and real property variations are used where they appear to be significant. Comparison is made to a simplified, coupled solution using a modified second-order one-dimensional diffusion equation for the radiative transfer. At the temperature levels assumed, radiative transfer may account for a greater portion of the total energy transfer over important portions of the nozzle, and its effects cannot, therefore, be neglected. Extreme energy flaxes (near 3XlO to the 8 Btu/(hr)(sq ft)) are observed for certain cases, and this implies that new nozzle cooling techniques must be developed.
Author : Richard L. Puthoff
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (31 download)
Download or read book A Design Study of a Regeneratively Cooled Nozzle for a Tungsten Water-moderated Nuclear Rocket System written by Richard L. Puthoff and published by . This book was released on 1966 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781720518440
Total Pages : 28 pages
Book Rating : 4.5/5 (184 download)
Download or read book Experimental Studies of the Heat Transfer to Rbcc Rocket Nozzles for Cfd Application to Design Methodologies written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-31 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Rocket thrusters for Rocket Based Combined Cycle (RBCC) engines typically operate with hydrogen/oxygen propellants in a very compact space. Packaging considerations lead to designs with either axisymmetric or two-dimensional throat sections. Nozzles tend to be either two- or three-dimensional. Heat transfer characteristics, particularly in the throat, where the peak heat flux occurs, are not well understood. Heat transfer predictions for these small thrusters have been made with one-dimensional analysis such as the Bartz equation or scaling of test data from much larger thrusters. The current work addresses this issue with an experimental program that examines the heat transfer characteristics of a gaseous oxygen (GO2)/gaseous hydrogen (GH2) two-dimensional compact rocket thruster. The experiments involved measuring the axial wall temperature profile in the nozzle region of a water-cooled gaseous oxygen/gaseous hydrogen rocket thruster at a pressure of 3.45 MPa. The wall temperature measurements in the thruster nozzle in concert with Bartz's correlation are utilized in a one-dimensional model to obtain axial profiles of nozzle wall heat flux.Santoro, Robert J. and Pal, SibtoshMarshall Space Flight CenterHEAT TRANSFER; ROCKET NOZZLES; COMPUTATIONAL FLUID DYNAMICS; LIQUID COOLING; HYDROGEN; OXYGEN; PROPELLANTS; HEAT FLUX; TEMPERATURE PROFILES; WALL TEMPERATURE
Author : Donald R. Boldman
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (31 download)
Download or read book Prediction of Local and Integrated Heat Transfer in Nozzles Using an Integral Turbulent Boundary Layer written by Donald R. Boldman and published by . This book was released on 1972 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: An empirical modification of an existing integral energy turbulent boundary layer method is proposed in order to improve the estimates of local heat transfer in converging-diverging nozzles and consequently, provide better assessments of the total or integrated heat transfer. The method involves the use of a modified momentum-heat analogy which includes an acceleration term comprising the nozzle geometry and free stream velocity. The original and modified theories are applied to heat transfer data from previous studies which used heated air in 30 deg - 15 deg, 45 deg - 15 deg, and 60 deg - 15 deg water-cooled nozzles.
Author : Richard J. Quentmeyer
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.:/5 (317 download)
Download or read book Hot-gas-side Heat Transfer Characteristics of Subscale, Plug-nozzle Rocket Calorimeter Chamber written by Richard J. Quentmeyer and published by . This book was released on 1993 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : John R. Jack
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (31 download)
Download or read book Feasibility of Optimizing Nozzle Performance for Orbital-launch Nuclear Rockets written by John R. Jack and published by . This book was released on 1963 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
