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Coupled numerical simulation of the external and engine inlet flows for the F-18 at large incidenceThis paper presents a numerical simulation of the external and engine inlet flows for the F-18 aircraft at typical high-angle-of-attack flight conditions. Two engine inlet mass flow rates, corresponding to flight idle and maximum power, were computed. This was accomplished using a structured, overset grid technique to couple the external and internal grid systems. Reynolds-averaged Navier-Stokes solutions were obtained using an implicit, finite-differencing scheme. Results show a strong coupling of the external and engine inlet flows, especially at the maximum power setting. Increasing the mass flow rate through the inlet caused the primary vortex breakdown location to move downstream. This trend is also observed in flight tests performed on the F-18. A reversed flow region upstream of the inlet duct is visible in the faired-inlet and flight-idle computations. This flow reversal is not present in the maximum power setting computation. These large-scale changes in flow structure highlight the importance of simulating inlet conditions in high-angle-of-attack aircraft computations.
Document ID
19920062869
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Murman, Scott M.
(MCAT Institute Moffett Field, CA, United States)
Rizk, Yehia M.
(NASA Ames Research Center Moffett Field, CA, United States)
Schiff, Lewis B.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-2621
Meeting Information
Meeting: AIAA Applied Aerodynamics Conference
Location: Palo Alto, CA
Country: United States
Start Date: June 22, 1992
End Date: June 24, 1992
Accession Number
92A45493
Funding Number(s)
CONTRACT_GRANT: NCC2-729
Distribution Limits
Public
Copyright
Other

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