Effect of propellant injection velocity on screech in 20,000-pound hydrogen-oxygen rocket engine
Propellant injection velocity effect on screech in 20,000 pound hydrogen-oxygen rocket engine
ROCKET ENGINE↗
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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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Carbon dioxide dissociation at 6000 deg to 11,000 deg K.
Shock tube measurements of carbon dioxide dissociation in argon mixtures at 6000 to 11,000 degrees K
THERMAL DISSOCIATION↗
High impact pressure regulator withstands impacts of over 15,000 g
High impact pressure regulator used with a high impact gas scannograph withstands impacts of over 15,000 g. By the passage of fluid through the first and second chambers of the regulator, the pressure of the scannograph is regulated from a specific input valve to the desired output pressure valve.
Biles, J. E., Jr.↗
Biochemical effects of prolonged exposure to an atmosphere of 100 percent oxygen at a simulated altitude of 27,000 feet
Biochemical responses of humans exposed to pure oxygen environment at simulated altitude of 27,000 feet
OXYGEN SYSTEM↗
The atmospheric transmission of infrared radiation from 2-5 microns for slant paths from 35,000 feet to the upper limit of the atmosphere, a survey
Atmospheric transmission of infrared radiation from 2 to 5 microns for slant paths between 35,000 feet and upper limit of atmosphere
UPPER ATMOSPHERE↗
Effects of jet pluming on the static stability of five rocket models at Mach numbers of 4, 5 and 6 and static pressure ratios up to 26,000
Jet pluming effect on static stability of five cone cylinder-flare finned rocket models at Mach numbers of 4, 5, and 6 and static pressure ratios up to 26,000
ROCKET EXHAUST↗
The effect of several injector face baffle configurations on screech in a 20,000-pound thrust hydrogen-oxygen rocket.
Effect of several injector face baffle configurations on screech in 20,000-lb thrust hydrogen-oxygen rocket
HYDROGEN OXYGEN /HOPE/ SPACECRAFT↗
Estimates of the Upper Limit of Ion Temperature in the 7000-30,000 Km Altitude Range According to Measurements Aboard AES ''elektron-2''
Elektron-2 measurements of upper limits of ion temperatures between 7000 and 30,000 km
Bezrukikh, V. V.↗
Atmospheric conditions associated with turbulence encountered by the XB-70 airplane above 40,000 feet altitude
Atmospheric conditions during turbulences encountered by XB-70 aircraft above 40,000 ft
Ehernberger, L. J.↗
Sky effect on solar cells calibrated at 80,000 feet
Sky radiation effects on output of solar cells at 80,000 feet
Ritchie, D. W.↗
Real-helium hypersonic flow parameters for pressures to 3600 atmospheres and temperatures to 15,000 deg K
Real helium hypersonic flow parameters for pressures to 3600 atmospheres and temperatures to 15,000 Deg K applicable to hotshot type wind tunnels
Miller, C. G., III↗
Parametric reentry study of elliptic earth orbits with apogees up to 10,000 nautical miles
Mathematical model of parametric reentry study of elliptic earth orbits with apogees up to 10,000 nautical miles
Pruett, W. R.↗
An estimate of line width and pressure from the high resolution spectrum of Jupiter at 11,000 angstrom units
Pressure and line width estimate from high resolution image tube spectra of Jupiter at 11,000 A
Farmer, C. B.↗
Meeting the challenge of a 50,000-hour-lifetime requirement
Materials and noncontacting design for 50,000 hour lifetime electromechanical components, noting magnetically suspended motor
Studer, P. A.↗
An extension of Frost's mixture rule to include the effects of multiple ionization on electrical conductivity - Application to equilibrium air at 3000 to 28,000 K
Expressions for electrical conductivity of plasmas applied to equilibrium air at 3000 to 28,000 K
Source record↗
SNAP-8 rotating machinery components - 10,000 hour endurance achievement
SNAP 8 turbine-alternator as nuclear-electric space power converter, discussing rotating machinery components design and 10,000 hr endurance testing results
Pope, J. R.↗
The thermodynamic properties of nitrogen from 65 to 2000 K with pressures to 10,000 atmospheres
An equation of state is presented for liquid and gaseous nitrogen for temperatures from 65 degrees K to 2000 degrees K and pressures to 10,000 atmospheres. All the pressure-density-temperature data available from published literature have been corrected and applied to bring experimental temperatures into accord with the International Practical Temperature Scale of 1968. The coefficients of the equation of state were determined by a weighted least squares fit to selected published pressure-density-temperature data. The methods of weighting the various data for simultaneous fitting are presented and discussed.
Jacobsen, R. T.↗
Scanner observations of cool stars from 3400 to 11,000 A.
Evaluation of photoelectric scans of the M supergiant alpha Ori and the carbon stars 19 Psc, W Ori, and DS Peg made at 20-A resolution from 3400 to 6000 A and at 40-A resolution from 6000 to 11,000 A. The data are corrected for atmospheric extinction and for the instrumental response to obtain plots of log flux per unit frequency interval versus wavelength. The dominant spectral features are due to C2, CN, and TiO; the variation of these features with spectral class is pointed out.
Fay, T.↗