RL10A-3-3 rocket engine oxidizer pump development program, August 1965 - June 1966
Carbon rug rings used to eliminate metal-metal rub of inducer on housings in rocket engine oxidizer pump
PUMP↗
SEARCH · Engineering Papers
Results for “rockets”
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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Study on the spectral emissivity of carbon particles produced by a rocket motor Final report
Spectral emissivity of carbon particles in exhaust gases of rocket engines using oxygen and RP-1 PROPELLANTS
SPECTRAL EMISSION↗
Results of sixteen differential absorption and Faraday rotation measurements with Nike-Apache rockets
D-layer differential absorption and Faraday rotation measurements with Nike-Apache rockets
FARADAY ROTATION↗
Frequency response and transfer functions of a nuclear rocket engine system obtained from analog computer simulation
Frequency response and transport functions for NERVA-type rocket engine
FREQUENCY RESPONSE↗
Spectral radiance measurements of rocket model exhaust gases, at simulated altitude, using a high speed scanning spectrometer Final report, part 2
Spectral radiance measurements of scale model rocket engine exhaust gases at simulated altitude using high speed scanning spectrometer
SCANNING DEVICE↗
An experimental correlation of the nonreactive properties of injection schemes and combustion effects in a liquid-propellant rocket engine. Part II. Instrumentation, experimental apparatus, and experimental techniques
Apparatus, techniques, and instrumentation for experimental correlation of nonreactive injection schemes and combustion effects in liquid propellant rocket engine
INJECTOR↗
Investigation of a submerged nozzle on a 1/14.2-scale model of the 260-inch solid rocket
Flow characteristics about submerged rocket nozzle model immersed in simulated exhaust gas
SUBMERGED BODY↗
Experimental evaluation of high-purity-silica reinforced ablative composites as nozzle sections of 7.8-inch-/19.8 CM/ diameter throat storable-propellant rocket engine
High purity silica reinforced ablative composite materials evaluated as nozzle sections of throat storable propellant rocket engine - erosion rates and charring
SILICON OXIDE↗
Pulse-train generator for rocket camera
Solid state, pulse-train generator to control shutter and film-advance timing in camera experiments on sounding rockets
SOUNDING ROCKET↗
A latitude survey of the equatorial electrojet with rocket-borne magnetometers
Rocket borne rubidium magnetometer measurements for latitude determination of equatorial electrojet
MAGNETOMETER↗
Application of Exhaust Diffusers for Rocket Engine Testing
Applications of exhaust diffusers for chemical propellant rocket engine testing
DIFFUSER↗
Simulation of gaseous core nuclear rocket mixing characteristics using cold and arc heated flows
Mixing phenomena of cold and arc heated jets from coaxial flows of helium or nitrogen related to gaseous core nuclear rockets
NUCLEAR ROCKET↗
Static stability investigation of a sounding-rocket vehicle at Mach numbers from 1.50 to 4.63
Static stability of sounding rocket at Mach numbers 1.50 to 4.63 to determine effect of body length and fin cant
STATIC STABILITY↗
The Formation and Properties of Liquid Sheets Suitable for Use in Rocket Engine Injectors
Formation and properties of liquid sheets suitable for use in rocket engine injectors
FLUID JET↗
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↗
Review of thermal radiation from liquid and solid propellant rocket exhausts
Thermal radiation from liquid and solid propellant rocket exhausts
SOLID PROPELLANT↗
The integrated-circuit control and timing system of the high-altitude rocket-radar project
Integrated circuit control and timing system of high altitude rocket radar
TIMING APPARATUS↗
Experimental investigation of base heating and rocket hinge moments for a simulated missile through a Mach number range of 0.8 to 2.0
Jet-stream interaction effects on rocket engine studied with simulated ballistic missile using liquid oxygen and JP-4 fuel mixture
JP-4 JET FUEL↗