A resonance-tube igniter for hydrogen-oxygen rocket engines
Resonance-tube igniter for hydrogen-oxygen rocket engines
HYDROX ENGINE↗
Engineering topics
Conrad, E. W.
Publications and source records attributed to Conrad, E. W..
M-1 injector development - Philosophy and implementation.
M-1 injector baffles, ablative chamber and start system design and development, using subscale testing
COMBUSTION EFFICIENCY↗
M-1 injector development - Philosophy and implementation
Subscale and full scale test firings of M-1 injector to improve combustion efficiency
COMBUSTION EFFICIENCY↗
Some injector element detail effects on screech in hydrogen-oxygen rockets
Concentric tube injection effect on dynamic characteristics of hydrogen-oxygen rocket
ROCKET THRUST↗
Cooled baffle development for M-1 engine using a subscale rocket engine
Film and transpiration cooled baffles for M-1 engine
Conrad, E. W.↗
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↗
Non-reusuable kinetic energy absorber Patent
Non-reusable kinetic energy absorber for application in soft landing of space vehicles
Conrad, E. W.↗
Thrust vector control apparatus Patent
Thrust vector control by secondary injection of fluid into rocket nozzle flow field to separate exhaust flow
Conrad, E. W.↗
Kinetic-energy absorber employs frictional force between mating cylinders
A kinetic energy absorbing device uses a series of coaxial, mating cylindrical surfaces. These surfaces have high frictional resistance to relative motion when axial impact forces are applied. The device is designed for safe deceleration of vehicles impacting on landing surfaces.
Conrad, E. W.↗
Stall and surge in turbojet engines
Explore the source record for details and available documents.
Gabriel, D. S.↗
Stall and surge in turbojet engines
Explore the source record for details and available documents.
Gabriel, D. S.↗
Stall and surge in turbojet engines
Explore the source record for details and available documents.
Gabriel, D. S.↗
Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine: Windmilling Characteristics - 2
Wind tunnel investigations were performed to determine the performance properties of an axial-flow gas turbine-propeller engine II. Windmilling characteristics were determined for a range of altitudes from 5000 to 35,000 feet, true airspeeds from 100 to 273 miles per hour, and propeller blade angles from 4 degrees to 46 degrees.
Conrad, E. W.↗
Preliminary Results of an Altitude-Wind-Tunnel Investigation of a TG-100A Gas Turbine-Propeller Engine II - Windmilling Characteristics
An investigation was conducted to determine the operational and performance characteristics of the TG-100A gas turbine-propeller engine II. Windmilling characteristics were deterined for a range of altitudes from 5000 to 35,000 feet, true airspeeds from 100 to 273 miles per hour, and propeller blade angles from 4 degrees to 46 degrees.
Conrad, E. W.↗