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Aerodynamic Considerations for Engine Inlet Design for Subsonic High Bypass Fan Engines
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English
Abstract
Consideration is given the manner in which inlet throat Mach number. cowl forebody lip suction loss, boattail pressure, and skin friction affect the design of nacelles for high bypass ratio, short duct engines. The mutual relationship of the fan nozzle, hot gas nozzle, the gas generator cowling, and the fan cowl is discussed.
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Citation
Viall, W., "Aerodynamic Considerations for Engine Inlet Design for Subsonic High Bypass Fan Engines," SAE Technical Paper 660733, 1966, https://doi.org/10.4271/660733.Also In
References
- Viall W. S. “Development of a Subsonic Diffusing Engine Inlet for the 707-120B/720B Airplanes.” Document D6-7588 The Boeing Co. Sept. 10 1962
- Klees G. W. “Subsonic Inlet Research and Development - Variable Concepts Applicable to 707 Airplanes with Advanced JT3D Fan Engines.” The Boeing Co. Oct. 15 1964
- Scherrer Richard Anderson Warren E. “Preliminary Investigation of a Family of Diffusers Designed for Near Sonic Inlet Velocities.” February 1956
- Schlicting H. “Boundary Layer Theory.” New York McGraw-Hill 1960
- Lawrence R. L. “Nacelle Cowling of High-Bypass-Ratio Turbofan Engines.” The Boeing Co. Jan. 5 1966
- Monk J. R. “Estimation of Subsonic Engine Nacelle Drag.” The Boeing Co. Sept. 5 1963
- Frazier G. T. “Aerodynamic Considerations for Engine Exhaust Design for Subsonic High Bypass Fan Engines.” SAE Trans. 75 1967 660734