Results of a theoretical and experimental study of the total pressure losses and combustion efficiencies associated with the divided-flow combustor are presented and comparisons made with the nondivided-flow combustor. The theoretical treatment indicated the range of primary-zone size, primary-zone air flow, and flame-holder pressure-loss coefficients over which the total-pressure loss through the divided-flow combustor was less than that through the nondivided-flow combustor. The experimental work indicated the range of fuel-air ratios, for a given size primary zone, over which the combustion efficiency in the divided-flow combustor was higher than that in the nondivided-flow combustor
An experimental investigation of a four-inlet side dump combustor configuration suitable for a boost...
Methods of introducing and distributing air and fuel in turbojet-engine combustors were evaluated wi...
One-dimensional analysis of variable area mixing and combustion process in supersonic ramjet and roc...
A ram-jet engine with an experimental 48-inch-diameter combustor was investigated in a free-jet faci...
The results of fuel-air ratio and temperature surveys made in the flame stabilizing zone of a 16-inc...
A preliminary evaluation was made of three types of combustor configurations in a 48-inch-diameter r...
Results obtained with three different burner configurations in a connected-pipe investigation of a 1...
A preliminary evaluation was made of three types of combustor con-figuration in a 48-inch-diameter r...
The ram jet is basically one of the most dimple types of aircraft engine. It consists only of an inl...
Aerodynamic considerations in the design of high performance combustors for turbojet engines are dis...
The effects of mass-flow ratio on the additive drag and normal-shock position of a single oblique-sh...
The liquid fuel ramjet system employing a subsonic side-dump combustor is simulated inthe present st...
An experimental investigation of combustor total-pressure loss was undertaken to confirm previous th...
The report describes the design of a piloted combustor intended for a ram-jet engine of long flight ...
Free jet tests of 48 inch diameter ramjet combustor with annular can-type flame holde
An experimental investigation of a four-inlet side dump combustor configuration suitable for a boost...
Methods of introducing and distributing air and fuel in turbojet-engine combustors were evaluated wi...
One-dimensional analysis of variable area mixing and combustion process in supersonic ramjet and roc...
A ram-jet engine with an experimental 48-inch-diameter combustor was investigated in a free-jet faci...
The results of fuel-air ratio and temperature surveys made in the flame stabilizing zone of a 16-inc...
A preliminary evaluation was made of three types of combustor configurations in a 48-inch-diameter r...
Results obtained with three different burner configurations in a connected-pipe investigation of a 1...
A preliminary evaluation was made of three types of combustor con-figuration in a 48-inch-diameter r...
The ram jet is basically one of the most dimple types of aircraft engine. It consists only of an inl...
Aerodynamic considerations in the design of high performance combustors for turbojet engines are dis...
The effects of mass-flow ratio on the additive drag and normal-shock position of a single oblique-sh...
The liquid fuel ramjet system employing a subsonic side-dump combustor is simulated inthe present st...
An experimental investigation of combustor total-pressure loss was undertaken to confirm previous th...
The report describes the design of a piloted combustor intended for a ram-jet engine of long flight ...
Free jet tests of 48 inch diameter ramjet combustor with annular can-type flame holde
An experimental investigation of a four-inlet side dump combustor configuration suitable for a boost...
Methods of introducing and distributing air and fuel in turbojet-engine combustors were evaluated wi...
One-dimensional analysis of variable area mixing and combustion process in supersonic ramjet and roc...