Add to ORKGSecondary atomization and ignition characteristics of aluminum/hydrocarbon gel propellants were investigated. Models of gel droplet shell formation were applied to aluminum/liquid hydrocarbon propellants to examine the effects of solid loading and ultimate particle size on the minimum droplet diameter permitting secondary atomization. A one-dimensional model of a gel-fueled rocket combustion chamber was developed. A model for radiant heat transfer from hot aluminum oxide particles to the chamber walls is included. A two-dimensional, two-phase nozzle code was used to estimate nozzle two-phase losses and overall engine performance
An experimental investigation to determine the effects of an accelerating gas flow on the atomizatio...
This project will present research which attempts to characterize the average droplet size of a two-...
The objective of this research is to create combustion data for gelled and metallized gelled fuels u...
A one-dimensional model of a gel-fueled rocket combustion chamber has been developed. This model inc...
A one-dimensional model of a hydrocarbon/Al/O2(gaseous) fueled rocket combustion chamber was develop...
The overall objective is the development of a fundamental understanding of the ignition and combusti...
Over the past six months, experimental investigations were continued and theoretical work on the sec...
A series of rocket engine heat transfer experiments using metallized gelled liquid propellants was c...
A set of analyses was conducted to determine the heat transfer characteristics of metallized gelled ...
Aluminized composite propellant used in solid rocket motors contain a lot of aluminium particles bec...
A series of combustion experiments using metallized gelled liquid propellants were conducted. These ...
A series of combustion experiments were conducted to measure the specific impulse, Cstar-, and speci...
A series of rocket engine heat transfer experiments using metallized gelled liquid propellants was c...
Research efforts are being conducted by the NASA Lewis Research Center to formulate and characterize...
A study was conducted at NASA-Lewis to compare the atomization characteristics of gelled and nongell...
An experimental investigation to determine the effects of an accelerating gas flow on the atomizatio...
This project will present research which attempts to characterize the average droplet size of a two-...
The objective of this research is to create combustion data for gelled and metallized gelled fuels u...
A one-dimensional model of a gel-fueled rocket combustion chamber has been developed. This model inc...
A one-dimensional model of a hydrocarbon/Al/O2(gaseous) fueled rocket combustion chamber was develop...
The overall objective is the development of a fundamental understanding of the ignition and combusti...
Over the past six months, experimental investigations were continued and theoretical work on the sec...
A series of rocket engine heat transfer experiments using metallized gelled liquid propellants was c...
A set of analyses was conducted to determine the heat transfer characteristics of metallized gelled ...
Aluminized composite propellant used in solid rocket motors contain a lot of aluminium particles bec...
A series of combustion experiments using metallized gelled liquid propellants were conducted. These ...
A series of combustion experiments were conducted to measure the specific impulse, Cstar-, and speci...
A series of rocket engine heat transfer experiments using metallized gelled liquid propellants was c...
Research efforts are being conducted by the NASA Lewis Research Center to formulate and characterize...
A study was conducted at NASA-Lewis to compare the atomization characteristics of gelled and nongell...
An experimental investigation to determine the effects of an accelerating gas flow on the atomizatio...
This project will present research which attempts to characterize the average droplet size of a two-...
The objective of this research is to create combustion data for gelled and metallized gelled fuels u...