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Life Cycle Cost Impact on Design Considerations for Civil
A New Development Concept for Gas Turbine Engine Optimize
The Development and Utilisation of an Engine Usage Monitoring
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achieved aerodynamic aircraft airframe analysis angle annular axial axial compressor blade row boundary layer bypass ratio calculation cascade characteristics coefficient combustion chamber combustor components compressor concept configuration cooling cost crossflow cruise cycle design variables DFVLR diffuser downstream droplet duct effects efficiency ejector emission engine equation estimated evaluation exit experimental failure flight fuel injection gas turbine geometry hypermixing increase injection inlet guide blades intake loss Mach number mass flow maximum measured method mission NASA nozzle obtained operating overall parameters performance plane pressure ratio problem procedure profiles ramjet range reduced requirements rocket rotating rotor scramjet secondary sensor shock wave shown in Figure specific specific fuel consumption specific impulse speed stage static pressure stator subsonic supersonic surge techniques terminal shock thrust tion total pressure transonic turbofan turbojet turbulent values variation velocity wall