Heat transfer in rocket nozzles using high temperature hydrogen propellant with real property variations.
Coupled radiative and convective heat fluxes in high temperature hydrogen propellant rocket nozzles with shape and temperature variations
SEARCH · Engineering Papers
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Coupled radiative and convective heat fluxes in high temperature hydrogen propellant rocket nozzles with shape and temperature variations
Photoelastic investigation on scaled models of Algol rocket engine nozzles to determine pressure and thermal stresses
Starting characteristics of M- I liquid propellant rocket engine using analog computer simulation
Black Brant II sounding rocket instrumentation for measurement of D layer electron density and collision rate
Performance characteristics of Aerobee sounding rocket and launch vehicle configuration
Flight tests of solid propellant rockets in dynamic spin or roll environments
Kiwi B nuclear rocket acoustics - sound pressure distribution, energy conversion, and power distribution
Survey of extraterrestrial nonsolar X-radiation by Aerobee rocket measurements
Photographs of earth night air glow obtained from Aerobee rocket
Thermal and pressure stress measurements for photoelastic model of Algol rocket nozzle
Ablative material evaluation for nozzle sections of storable propellant rocket engine
Payload weight and length effect on mass and aerodynamic characteristics of Apache and Cajun sounding rockets
Attitude control system equipped Aerobee rocket study of stellar X-ray emissions
Solid propellant rocket exhaust effects and methods of attenuation - project summary
Radiological prediction and monitoring of tests at Nuclear Rocket Development Station
Liquid hydrogen flow system performance during startup transient of nuclear rocket measured in full-scale simulated engine system, approximating in-flight exhaust conditions
Coupled radiative and convective heat fluxes in high temperature hydrogen propellant rocket nozzles with shape and temperature variations
Parameter adjustment model reference adaptive control of nuclear rocket engine, noting design parameters, system performance, propellant savings estimates and dynamic stability