Accession Number N20130011042
Title Simulating Effects of High Angle of Attack on Turbofan Engine Performance.
Publication Date Feb 2013
Media Count 24p
Personal Author J. S. Litt R. W. Claus T. H. Guo Y. Liu
Abstract A method of investigating the effects of high angle of attack (AOA) flight on turbofan engine performance is presented. The methodology involves combining a suite of diverse simulation tools. Three-dimensional, steady-state computational fluid dynamics (CFD) software is used to model the change in performance of a commercial aircraft-type inlet and fan geometry due to various levels of AOA. Parallel compressor theory is then applied to assimilate the CFD data with a zero-dimensional, nonlinear, dynamic turbofan engine model. The combined model shows that high AOA operation degrades fan performance and, thus, negatively impacts compressor stability margins and engine thrust. In addition, the engine response to high AOA conditions is shown to be highly dependent upon the type of control system employed.
Keywords Angle of attack
Computational fluid dynamics
Computerized simulation
Dimensional analysis
Dynamic models
Flight characteristics
Simulation
Steady state
Thrust
Turbofan engines


 
Source Agency National Aeronautics and Space Administration
NTIS Subject Category 51C - Aircraft
Corporate Author National Aeronautics and Space Administration, Cleveland, OH. NASA John H. Glenn Research Center at Lewis Field.
Document Type Technical report
Title Note N/A
NTIS Issue Number 1320
Contract Number N/A

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