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.
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.
Download or read book Analysis of Heat transfer Effects in Rocket Nozzles Operating with Very High temperature Hydrogen with List of References written by and published by . This book was released on 1965 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Analysis Feasibility and Wall temperature Distribution of a Radiation cooled Nuclear rocket Nozzle written by William H. Robbins and published by . This book was released on 1962 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Analysis of Thermal Radiation Heat Transfer in a Nuclear rocket Nozzle written by William H. Robbins and published by . This book was released on 1961 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Heat transfer Study of a Regeneratively Cooled Hydrogen fluorine Rocket Engine at Low Chamber Pressure written by and published by . This book was released on 1967 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
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 Adm Nasa and published by Independently Published. This book was released on 2018-09-15 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
Download or read book NASA Technical Report written by and published by . This book was released on 1965 with total page 662 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Analysis of the Effect of a Seeded Propellant Layer on Thermal Radiation in the Nozzle of a Gaseous core Nuclear Propulsion System written by John R. Howell and published by . This book was released on 1965 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 836 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government wide Index to Federal Research Development Reports written by and published by . This book was released on 1966 with total page 1466 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Analysis Feasibility and Wall temperature Distribution of a Radiation cooled Nuclear rocket Nozzle written by William H. Robbins and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis was made to determine the feasibility of operating radiation-cooled nuclear-rocket nozzles with hydrogen as the propellant. Walltemperature distributions and heat fluxes along the nozzle were calculated by two techniques. One wall-temperature distribution was obtained from a simplified heat balance which included only the convection into the wall and the radiation from the wall. A more refined calculation was made for wall temperature in which the heat balance also included the radiation inside the nozzle and the axial and radial heat conduction. The agreement between the two solutions of temperature distribution was excellent in the divergent portion of the nozzle. The average temperature difference over the range of pressure and area ratio investigated was approximately 1 percent. In the convergent section large differences in temperature between the two solutions were observed, because the radiant heat flux from the reactor to the nozzle was neglected in the simplified solution. (Author).
Download or read book NASA Technical Note written by and published by . This book was released on 1965 with total page 348 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Analysis of the Transient Radiation Heat Transfer of an Uncooled Rocket Engine Operating Outside Earth s Atmosphere written by William H. Robbins and published by . This book was released on 1959 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Monthly Catalog of United States Government Publications Cumulative Index written by United States. Superintendent of Documents and published by . This book was released on 1979 with total page 1250 pages. Available in PDF, EPUB and Kindle. Book excerpt:
