SEARCH · Search NASA
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.
Saturn V/S-IVB stage low gravity fluid mechanics problems and Saturn IB liquid hydrogen orbital experiment to verify propellant ullaging and orbital venting system
Striated cone structure resembling shatter cones in volcanic vent near Albuquerque, New Mexico
Hydrogen vent flare stack performance in adverse weather conditions
Low leakage rate, large diameter vent and relief valve operates satisfactorily over a large temperature range by a design that accommodates waviness and distortions due to thermal gradients. It is based on a fixed sealing member having an inclined lapped surface to which a flexible flow gate conforms.
Wall temperatures and heat transfer coefficients for solid-vapor mixtures of para hydrogen and nitrogen venting under low pressure
Computer program to determine pressure and pipe flow heat transfer in vented launch vehicle compartments during ascending flight
Characteristics of liquid metal cooled reactor gaseous fission products vented or contained, for space power systems
Supersonic wind tunnel tests of orifice venting characteristics and three dimensional flow on flat plates
Liquid hydrogen propellant dynamic and thermodynamic behavior during task venting in orbiting Saturn S-4B stage
Hydrogen-oxygen system high altitude explosion properties in vented tanks, discussing explosion hazard
Uranium dioxide vent loss in externally fueled thermionic reactor concept
Design, fabrication, and tests of prototype cryogenic zero-gravity heat exchanger vent system
Rate of loss of uranium dioxide or uranium mononitride from vented nuclear fuel element
Design and performance of liquid oxygen tank vent and relief valve
Flow characteristics of orifices for venting launch vehicle compartments
Simulation of two phase hydrogen venting to space environment, discussing thrust effect measurements, flow instabilities and instrumentation
Impingement pressure analysis associated with two phase cryogenic propellant venting to space environment