Rarefied gas dynamics
Monte Carlo method, and radiant heat transfer to analyze impact pressure probes
RAREFIED GAS DYNAMICS↗
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Results for “RADIANT HEATING”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Radiation from carbon in a rocket plume mixing region with coupled convective and radiative energy fluxes and general optical thickness
Carbon radiant heat transfer from plume mixing region to base of rocket vehicle
RADIATIVE HEAT TRANSFER↗
Estimates of local and average fuel temperatures in a gaseous nuclear rocket engine
Diffusion analysis on radiant heat transfer from gaseous nuclear fuel container to annulus of flowing hydrogen
NUCLEAR FUEL↗
Boundary-layer combustion in propulsion.
Propulsion-oriented subsonic boundary layer combustion research, discussing turbulent and diffusion-limited conditions, radiant heat transfer, chemical kinetics and transient phenomena
RADIATIVE HEAT TRANSFER↗
A Technique for Determining the Spatial Distribution of Relative Radiant Intensity in Shock Layers over Bodies at Angle of Attack at Hyersonic Velocities
Spatial distribution of radiant heat in reentry vehicle hypersonic shock layers at angle of attack
Reynolds, R. M.↗
Thermal radiation shields for piping in vacuum environments
System of thermal radiation shielding reduces radiant heat transfer in vacuum installations containing piping which carries working fluids. Method employs successive layers of spacers and rolled metal shields which are easily installed or removed, expedites efficient removal of entrapped gases, and adapts easily to small pipings.
Spagnuolo, A. C.↗
A comparison of two methods of measuring particle size of Al2O3 produced by a small rocket motor
The size of aluminum oxide particles produced by small rocket motors is determined by tank collection and spectrophotometry. The size of the particulate determines loss in thrust due to particle lag, particulate radiant heat transfer, acoustic attenuation and impingement and rocket plume structure and properties.
Dobbins, R. A.↗
Prediction of radiation from rocket exhaust gases
Rocket exhaust gases radiant heat transfer prediction, using band models with computer program
Reardon, J. E.↗
On dimensional line radiative transfer
Integrations over solid angle and frequency are performed in the expressions for the radiant heat flux and local energy loss of a line in a region of strong variations of the source function in one direction. Approximations are given for coefficients and kernels in the resulting forms which involve integrals over the physical coordinate.
Harstad, K. G.↗
Symposium on Uranium Plasmas: Research and Applications, 2nd, Atlanta, Ga., November 15-17, 1971, Collection of Technical Papers.
Results of theoretical and applied research related to fissioning uranium plasmas. Topics examined include uranium plasma instabilities, diagnostic techniques, radiant heat transfer characteristics, nuclear pumping of lasers, and various fission engine concepts. Engineering aspects considered for open-cycle gas core engines include effects of buoyancy on fuel containment, flow and criticality problems, effects of injection conditions, and radiation hazards. The nuclear light bulb engine, the mini-cavity reactor, the dust-bed reactor, and the colloid core reactor are also examined in terms of design and control considerations. Individual items are abstracted in this issue.
Source record↗
Opacity of tungsten-seeded hydrogen to 2500 K and 115 atmospheres.
Experimental investigation and measurement of the radiant heat attenuation of an aerosol which may serve as a gas core nuclear-rocket propellant. The experiment uses a tungsten-hydrogen aerosol heated to temperatures as high as 2500 K under pressures up to 115 atmospheres. The hydrogen aerosol is produced by dispersion of submicron-sized particles of tungsten in hydrogen gas. A narrow beam of broad spectrum (visible and ultraviolet) light is passed through it with the attenuation being measured as a function of wavelength. Other aerosol characteristics examined include the nature and extent of chemical reactions between the seed material and the hydrogen and the degree of dispersion of the seed material obtained before and after heating. Chemical equilibrium calculations and vapor pressure data for the refractory metals indicate that tungsten is a prime candidate for the seed material in the gas core nuclear rocket.
Williams, J. R.↗
Measurements of seeded argon-hydrogen plasma properties.
Seeded argon-hydrogen plasmas have been produced at Georgia Tech in order to experimentally measure composition, temperature, radiant heat output and opacity. The plasma, seeded with submicron tungsten particles, simulates the propellant of a gaseous core nuclear rocket. These measurements are needed to predict the dynamic behavior of the operating gas core reactor. The temperature range in which the seed has vaporized but the hydrogen itself has not yet become opaque is known as the seed-hydrogen opacity window. Preliminary opacity data in this temperature range will be presented.
Benns, R. A.↗
Radiative transfer effects on reflected shock waves. II - Absorbing gas.
Radiative cooling effects behind a reflected shock wave are calculated for an absorbing-emitting gas by means of an expansion procedure in the small density ratio across the shock front. For a gray gas shock layer with an optical thickness of order unity or less the absorption integral is simplified by use of the local temperature approximation, whereas for larger optical thicknesses a Rosseland diffusion type of solution is matched with the local temperature approximation solution. The calculations show that the shock wave will attenuate at first and then accelerate to a constant velocity. Under appropriate conditions the gas enthalpy near the wall may increase at intermediate times before ultimately decreasing to zero. A two-band absorption model yields end-wall radiant-heat fluxes which agree well with available shock-tube measurements.
Su, F. Y.↗
An analytical and experimental evaluation of shadow shields and their support members.
Review of the major results of an analytical and experimental program aimed at determining the potential effectiveness of shadow shields in minimizing radiant heat transfer into cryogenic propellant tanks on long-duration interplanetary missions, taking into account the thermal interaction between shields and their support structures. Analytical procedures are developed and applied that include the strut-shield interaction in predicting shadow shield performance. The results of experimental studies of the effects of configuration variables on the performance of a scale model of a shadow shield system are presented. The experimental results are used to verify the validity of analytical predictions. The results obtained show that: (1) shadow shields can be effective in reducing the heat transfer into cryogenic propellant tanks, and (2) the conductive heat transfer through supports can be reduced by selective surface coatings.
Stochl, R. J.↗
Space radiator simulation manual for computer code
A computer program that simulates the performance of a space radiator is presented. The program basically consists of a rigorous analysis which analyzes a symmetrical fin panel and an approximate analysis that predicts system characteristics for cases of non-symmetrical operation. The rigorous analysis accounts for both transient and steady state performance including aerodynamic and radiant heating of the radiator system. The approximate analysis considers only steady state operation with no aerodynamic heating. A description of the radiator system and instructions to the user for program operation is included. The input required for the execution of all program options is described. Several examples of program output are contained in this section. Sample output includes the radiator performance during ascent, reentry and orbit.
Black, W. Z.↗
Analytical design and performance studies of nuclear furnace tests of small nuclear light bulb models
Analytical studies were continued to identify the design and performance characteristics of a small-scale model of a nuclear light bulb unit cell suitable for testing in a nuclear furnace reactor. Emphasis was placed on calculating performance characteristics based on detailed radiant heat transfer analyses, on designing the test assembly for ease of insertion, connection, and withdrawal at the reactor test cell, and on determining instrumentation and test effluent handling requirements. In addition, a review of candidate test reactors for future nuclear light bulb in-reactor tests was conducted.
Latham, T. S.↗
Cavity temperature and flow characteristics in a gas-core test reactor
A test reactor concept for conducting basic studies on a fissioning uranium plasma and for testing various gas-core reactor concepts is analyzed. The test reactor consists of a conventional fuel-element region surrounding a 61-cm-(2-ft-) diameter cavity region which contains the plasma experiment. The fuel elements provide the neutron flux for the cavity region. The design operating conditions include 60-MW reactor power, 2.7-MW cavity power, 200-atm cavity pressure, and an average uranium plasma temperature of 15,000 K. The analytical results are given for cavity radiant heat transfer, hydrogen transpiration cooling, and uranium wire or powder injection.
Putre, H. A.↗
Handbook of infrared radiation from combustion gases
The treatment of radiant emission and absorption by combustion gases are discussed. Typical applications include: (1) rocket combustion chambers and exhausts, (2) turbojet engines and exhausts, and (3) industrial furnaces. Some mention is made of radiant heat transfer problems in planetary atmospheres, in stellar atmospheres, and in reentry plasmas. Particular consideration is given to the temperature range from 500K to 3000K and the pressure range from 0.001 atmosphere to 30 atmospheres. Strong emphasis is given to the combustion products of hydrocarbon fuels with oxygen, specifically to carbon dioxide, water vapor, and carbon monoxide. In addition, species such as HF, HC1, CN, OH, and NO are treated.
Ludwig, C. B.↗