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Record 27 of 466
Coupled numerical simulation of the external and engine inlet flows for the F-18 at large incidence
Author and Affiliation:
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)
Abstract: This 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.
Publication Date: Jan 01, 1992
Document ID:
19920062869
(Acquired Nov 22, 1995)
Accession Number: 92A45493
Subject Category: AERODYNAMICS
Report/Patent Number: AIAA PAPER 92-2621
Document Type: Conference Paper
Publication Information: SEE A92-45476
Publisher Information: United States
Meeting Information: 10th AIAA Applied Aerodynamics Conference; June 22-24, 1992; Palo Alto, CA; United States
Contract/Grant/Task Num: NCC2-729
Financial Sponsor: NASA; United States
Organization Source: NASA Ames Research Center; Moffett Field, CA, United States
Description: 9p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: ANGLE OF ATTACK; COMPUTATIONAL GRIDS; COMPUTERIZED SIMULATION; ENGINE INLETS; F-18 AIRCRAFT; INLET FLOW; FINITE DIFFERENCE THEORY; FLIGHT TESTS; NAVIER-STOKES EQUATION; VORTEX BREAKDOWN
Imprint And Other Notes: IN: AIAA Applied Aerodynamics Conference, 10th, Palo Alto, CA, June 22-24, 1992, Technical Papers. Pt. 1 (A92-45476 19-02). Washington, DC, American Institute of Aeronautics and Astronautics, 1992, p. 192-200.
Availability Source: Other Sources
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