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 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 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 An Analysis of Nuclear rocket Nozzle Cooling written by William H. Robbins and published by . This book was released on 1960 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: A nuclear-rocket regenerative-cooling analysis was conducted over a range of reactor power of 46 to 1600 megawatts and is summarized herein. Although the propellant (hydrogen) is characterized by a large heat-sink capacity, an analysis of the local heat-flux capability of the coolant at the nozzle throat indicated that, for conventional values of system pressure drop, the cooling capability was inadequate to maintain a selected wall temperature of 1440 R. Several techniques for improving the cooling capability were discussed, for example, high pressure drop, high wall temperature, refractory wall coatings, thin highly conductive walls, and film cooling. In any specific design a combination of methods will probably be utilized to achieve successful cooling.
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 Digital Codes for Design and Evaluation of Convectively Cooled Rocket Nozzle with Application to Nuclear type Rocket written by John E. Rohde and published by . This book was released on 1967 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 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:
Download or read book Thermal Fatigue Analysis of a Cryogenically Cooled Rocket Nozzle written by and published by . This book was released on 1967 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Cooldown Characteristics of Regenerative Nozzle Used in Full scale Cold flow Nuclear Rocket Test Facility written by George E. Turney and published by . This book was released on 1967 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
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 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 Wall Temperature Distribution Calculation for a Rocket Nozzle Contour written by Satoaki Omori and published by . This book was released on 1972 with total page 105 pages. Available in PDF, EPUB and Kindle. Book excerpt: The JANNAF turbulent boundary layer (TBL) computer program, applicable to rocket nozzles, requires a wall temperature distribution among other input parameters to determine boundary layer behavior, heat transfer, and performance degradation. The inclusion of a complete regenerative cooling cycle model with associate geometry, material and fluid property data provides a capability to internally calculate wall temperature profiles on the hot gas and coolant flow-side, as well as the coolant flow bulk temperature variation. Besides the regular heat transfer and performance degradation calculations, the new concept can be used to optimize the cooling cycle, flow requirements, and cooling jacket geometry.
Download or read book Comparison of Predicted Nozzle Coolant Side Heat Transfer and Fluid Flow with Experimental Values from Phoebus 2A Nuclear Tests written by Maynard F. Taylor and published by . This book was released on 1969 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Numerical Simulation of Film Cooled Ablative Rocket Nozzles written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-10-21 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this research effort was to evaluate the impact of incorporating an additional cooling port downstream between the injector and nozzle throat in the NASA Fast Track chamber. A numerical model of the chamber was developed for the analysis. The analysis did not model ablation but instead correlated the initial ablation rate with the initial nozzle wall temperature distribution. The results of this study provide guidance in the development of a potentially lighter, second generation ablative rocket nozzle which maintains desired performance levels. Landrum, D. B. and Beard, R. M. Marshall Space Flight Center NAG8-1097...
Download or read book Wall Temperature Distribution Calcilation for a Rocket Nozzle Contour written by Satoaki Omori and published by . This book was released on 1972 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt:
