Effects of Fuel-nozzle Carbon Deposition on Combustion Efficiency of Single Tubular-type, Reverse-flow Turbojet Combustor at Simulated Altitude Conditions PDF Download
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Author: Ralph T. Dittrich Publisher: ISBN: Category : Carbon Languages : en Pages : 34
Book Description
A study was made to determine the cause of irreproducibility of combustion data of a single tubular-type turbojet combustor operating at simulated altitude conditions.
Author: Ralph T. Dittrich Publisher: ISBN: Category : Carbon Languages : en Pages : 34
Book Description
A study was made to determine the cause of irreproducibility of combustion data of a single tubular-type turbojet combustor operating at simulated altitude conditions.
Author: Edward G. Stricker Publisher: ISBN: Category : Aeronautics Languages : en Pages : 28
Book Description
The combustion efficiency and the altitude operational limits of three liquid hydrocarbon fuels having high volumetric energy content (decalin, tetralin, and monomethylnaphthalene) were compared with an AN-F-58 fuel in a single tubular combustor from a J33 turbojet engine. The investigation covered a range of simulated engine conditions for altitudes from 20,000 to 60,000 feet; 42- to 107-percent normal rated engine speed; and a flight Mach number of 0.6. The independent effects of combustor-inlet-air temperature, pressure, and mass air flow on the combustion efficiency of the fuels were determined around a standard combustion-inlet condition.
Author: Warren A. Tucker Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 738
Book Description
A theoretical analysis, based on the linearized equation for supersonic flow, of characteristics of triangular-tip control surfaces on thin triangular wings. By restriction to case for which Mach lines from wing apex lie behind the leading edge, a simplified treatment was possible; results of previous work on lift of triangular wings could be used to derive expressions for lift effectiveness, pitching moment, rolling-moment effectiveness, hinge moment due to control deflection, and hinge moment due to angle of attack. Comparisons were made with two-dimensional case.
Author: Ralph T. Dittrich
Author: Ralph T. Dittrich
Author: Ralph T. Dittrich
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: Jerrold D. Wear
Author: Edward G. Stricker
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: Warren A. Tucker
Author: