Add to ORKGThin film, heat flux probe for measuring gas velocities in unstable rocket combusto
A priori prediction of rocket engine combustor flowfields is extremely difficult due to a number of ...
Data were taken with a film-cooled test plate placed in the exhaust stream of a rectangular combusto...
Prototype thin film heat flux sensors have been constructed and tested. The sensors can be applied t...
A new thin-film heat flux gage has been fabricated specifically for severe high temperature operatio...
A small laboratory diagnostic thruster was developed to augment present low thrust chemical rocket o...
The application of laser-based diagnostic techniques has become commonplace to a wide variety of com...
As a demonstration of technology maturation, a thin-film temperature sensor probe was fabricated and...
Among the important parameters which characterize the rocket flames are the (1) velocity, (2) pressu...
A cooled-gas pyrometer designed for application in a hypersonic research engine program was fabricat...
The mixing and heat transfer phenomena in small rocket flow fields with fuel film cooling is not wel...
The gas flow near the injector of a liquid propellant rocket was investigated by rapidly inserting b...
In-like transducers system measures flow rate of chemically active propellant fluids. The system use...
Hot-gas side heat-transfer rates for liquid oxygen and hydrogen propellant rocket nozzl
The Space Shuttle Main Engine (SSME) turbine environment stresses engine components to their design ...
A new automated, computer controlled heat flux measurement facility is described. Continuous transie...
A priori prediction of rocket engine combustor flowfields is extremely difficult due to a number of ...
Data were taken with a film-cooled test plate placed in the exhaust stream of a rectangular combusto...
Prototype thin film heat flux sensors have been constructed and tested. The sensors can be applied t...
A new thin-film heat flux gage has been fabricated specifically for severe high temperature operatio...
A small laboratory diagnostic thruster was developed to augment present low thrust chemical rocket o...
The application of laser-based diagnostic techniques has become commonplace to a wide variety of com...
As a demonstration of technology maturation, a thin-film temperature sensor probe was fabricated and...
Among the important parameters which characterize the rocket flames are the (1) velocity, (2) pressu...
A cooled-gas pyrometer designed for application in a hypersonic research engine program was fabricat...
The mixing and heat transfer phenomena in small rocket flow fields with fuel film cooling is not wel...
The gas flow near the injector of a liquid propellant rocket was investigated by rapidly inserting b...
In-like transducers system measures flow rate of chemically active propellant fluids. The system use...
Hot-gas side heat-transfer rates for liquid oxygen and hydrogen propellant rocket nozzl
The Space Shuttle Main Engine (SSME) turbine environment stresses engine components to their design ...
A new automated, computer controlled heat flux measurement facility is described. Continuous transie...
A priori prediction of rocket engine combustor flowfields is extremely difficult due to a number of ...
Data were taken with a film-cooled test plate placed in the exhaust stream of a rectangular combusto...
Prototype thin film heat flux sensors have been constructed and tested. The sensors can be applied t...