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.
Injector radial distribution and thrust chamber geometry effect on acoustic mode instability in hydrogen oxygen engines
Variable geometry features applied to lifting spacecraft to overcome inherent incompatibility and provide low speed and tangential landing capabilities
Aerodynamic and flight characteristics of variable geometry entry spacecraft during subsonic wing deployment and landing
Gas core reactor curved porous walls geometry tested with clear and smoky air injection, noting mass flow ratio in reactor cavity
Computer programming for graphic display of combinatorial geometry
Variable geometry design of minimal correction V/STOL wind tunnels
Reaction geometry in oxidation and reduction of alkaline silver electrodes
Low subsonic aerodynamic characteristics of medium hypersonic L/D reentry spacecraft configuration with variable geometry wing
Transonic aerodynamic characteristics of variable geometry reentry vehicle with hypersonic lift drag ratio
Reaction geometry in oxidation and reduction of alkaline silver electrode
Variable geometry inlet guide vanes and stators for extending stable operation of supersonic cruise turbine engine compressor front stage
Parametric design study of self-acting pad geometries for shaft seals in turbocompressors
Fixed geometry wind tunnel model of auxiliary inlet ejector with clamshell flow diverter from Mach 0 to 1.2
Electron microscopic studies of reaction geometry in oxidation and reduction of alkaline silver electrodes
Probe geometry effects on hot film anemometer probe performance during turbulence measurements in liquids
Liquid rocket engine injector elements design criteria, using noncircular orifice geometry to predict efficiency
Mercury electron bombardment thrustor, measuring effect of geometry and magnetic field inside pole piece region on discharge losses and propulsion efficiency
Computer program calculates trajectories of orbiting spacecraft and lander vehicles simultaneously. Using data from both vehicles, program calculates communications geometry which consists of orbiting spacecraft cone/clock angle, lander cone/clock angle, range, range rate and acceleration, and fade, reflective, and system margins.