One of the important issues in the assessment of the Net/engine compatibility in turbofan engines is to predict the coupling effects between the non-uniform inlet and engine. The computational method using an actuator-disk model has been applied to the calculations of the flow through a civil high-bypass-ratio turbofan engine with drooped intake and the flow through a multistage turbofan engine subjected to non-uniform total pressure inlet flow. The results of a series of calculations are presented and the nature of the interactions between the flow through a fan and non-uniform inlet flow is addressed.
G, J. (2001). THE APPLICATION OF ACTUATOR DISKS TO THE CALCULATION OF NON-UNIFORM FLOWS IN TURBOFAN ENGINES. International Conference on Aerospace Sciences and Aviation Technology, 9(ASAT Conference, 8-10 May 2001), 1-16. doi: 10.21608/asat.2001.24775
MLA
JOO W G. "THE APPLICATION OF ACTUATOR DISKS TO THE CALCULATION OF NON-UNIFORM FLOWS IN TURBOFAN ENGINES". International Conference on Aerospace Sciences and Aviation Technology, 9, ASAT Conference, 8-10 May 2001, 2001, 1-16. doi: 10.21608/asat.2001.24775
HARVARD
G, J. (2001). 'THE APPLICATION OF ACTUATOR DISKS TO THE CALCULATION OF NON-UNIFORM FLOWS IN TURBOFAN ENGINES', International Conference on Aerospace Sciences and Aviation Technology, 9(ASAT Conference, 8-10 May 2001), pp. 1-16. doi: 10.21608/asat.2001.24775
VANCOUVER
G, J. THE APPLICATION OF ACTUATOR DISKS TO THE CALCULATION OF NON-UNIFORM FLOWS IN TURBOFAN ENGINES. International Conference on Aerospace Sciences and Aviation Technology, 2001; 9(ASAT Conference, 8-10 May 2001): 1-16. doi: 10.21608/asat.2001.24775
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