The effects of chemical and physical parameters on the burning rate of a liquid droplet
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Lorell, J.↗
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An investigation of near critical and super- critical burning of fuel droplets Annual report
Combustion characteristics of liquid propellant droplets in air at near critical and super- critical pressures
Dominicis, D. P.↗
The effect of mixing, radiation, and finite rate combustion upon the flow field and surroundings of the exhaust plumes of rocket engines burning RP1 /kerosene/ and liquid oxygen
Shear layer mixing, hydrocarbon oxidation, and carbon cloud radiation models for liquid rocket engine exhaust plume analysis
Edelman, R.↗
Burn-rate testing apparatus
Combustibility tester fits into a sealed chamber so that tests may be performed under controlled atmospheric pressure and compostion. Support frame allows rotation of the test sample so that ignition combustion may be tested in various orientations from horizontal to vertical.
Dawn, F. S.↗
Photographic study of solid propellants burning in an acceleration environment Final report
Acceleration effects on aluminized composite solid propellants combustion by high speed color cinematography
Baker, K. L.↗
Quenching and extinguishment of burning solids in oxygen-enriched atmospheres Final report
Quenching distances for flaming thin polymer films, and fire extinguisher using inert gas to reduce fire hazards in spacecraft cabin atmospheres
Durfee, R. L.↗
A quasi-global chemical kinetic model for the finite rate combustion of hydrocarbon fuels with application to turbulent burning and mixing in hypersonic engines and nozzles.
Chemical kinetic model for hydrocarbon fuels combustion and application to multidimensional finite difference mixing analyses in hypersonic engines and nozzles
Edelman, R. B.↗
Vapor-phase combustion phenomena when Zr droplets burn in oxygen.
Laser ignited combustion of 365 micron Zr droplets falling in ultrapure oxygen using spectroscopic and photographic techniques, discussing vapor phase transport phenomena
Marshall, R. L.↗
Development of a propane burning annular combustor for use in a miniature gas turbine engine
Propane annular combustor for use in miniature gas turbine engine for wind tunnels
Burnett, M.↗
Reactions near the burning surface of double- base propellants
Reaction heat for flameless combustion of double- base propellant using differential scanning calorimetry and thermogravimetric analysis, noting pressure effects
Kirby, C. E.↗
Hydrogen Flare Stack Diffusion Flames - Low and High Flow Instabilities, Burning Rates, Dilution Limits, Temperatures, and Wind Effects
Combustion characteristics and safety factors for hydrogen diffusion flames in flare stack operations
Grumer, J.↗
Effect of fuel distribution and flame stabilization techniques on combustion stability limits for swirl-can combustor modules burning ASTM-A1 fuel
Effect of fuel distribution and flame stabilization techniques on combustion stability limits for swirl-can combustor modules
Briehl, D. C.↗
Burning of Teflon-insulated wires in supercritical oxygen at normal and zero gravities
Combustion properties of Teflon insulated wires in supercritical oxygen at normal and zero gravities
Andracchio, C. R.↗
Response of convectively controlled burning to nonlinear disturbances
Numerical analysis of energy release rates during combustion caused by periodic flow field disturbances
Heidmann, M. F.↗
Reactions near the burning surface of double- base propellants
Reaction heat for flameless combustion of double- base propellant using differential scanning calorimetry and thermogravimetric analysis, noting pressure effects
Kirby, C. E.↗
Photographic study of solid propellants burning in an acceleration environment
Photographic study of acceleration and pressure effects on Al agglomerates and combustion processes on solid propellant surface, describing pit growth by combustion model
Baker, K. L.↗
A Monte Carlo error analysis program for near-Mars, finite-burn, orbital transfer maneuvers
A computer program was developed which performs an error analysis of a minimum-fuel, finite-thrust, transfer maneuver between two Keplerian orbits in the vicinity of Mars. The method of analysis is the Monte Carlo approach where each off-nominal initial orbit is targeted to the desired final orbit. The errors in the initial orbit are described by two covariance matrices of state deviations and tracking errors. The function of the program is to relate these errors to the resulting errors in the final orbit. The equations of motion for the transfer trajectory are those of a spacecraft maneuvering with constant thrust and mass-flow rate in the neighborhood of a single body. The thrust vector is allowed to rotate in a plane with a constant pitch rate. The transfer trajectory is characterized by six control parameters and the final orbit is defined, or partially defined, by the desired target parameters. The program is applicable to the deboost maneuver (hyperbola to ellipse), orbital trim maneuver (ellipse to ellipse), fly-by maneuver (hyperbola to hyperbola), escape maneuvers (ellipse to hyperbola), and deorbit maneuver.
Green, R. N.↗
Investigation of the Ignition and Burning of Materials in Space Cabin Atmospheres. Part 2: Ignition of a Combustible Mixture by a Hot Body with the Effects of Gravity
The ignition of a combustible gas mixture by a hot cylinder under the effect of a gravity field for steady state conditions is examined. For this purpose a horizontal cylinder is considered with gravity as a parameter together with a finite chemical reacting flow generated by free convection with the additional effect of diffusion. Both mass transfer and zero mass transfer cases are considered. By defining an ignition criterion the surface temperature and species are obtained from the analysis as a function of the gravity field. It is supposed that at the point of ignition the heat evolved in the gas is sufficiently high to attain a sustained combustion without any energy from the hot cylinder.
Lew, H. G.↗