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Numerical Simulation of F-18 Fuselage Forebody Flows at High Angles of Attack
Proceedings of the NASA CFD Conference
  • Lewis B. Schiff, NASA Ames Research Center
  • Russell M. Cummings, NASA Ames Research Center
  • Reese L. Sorenson, NASA Ames Research Center
  • Yehia M. Rizk, NASA Ames Research Center
Publication Date
3-1-1989
Abstract

As part of the NASA High Alpha Technology Program, fine-grid Navier-Stokes solutions have been obtained for flow over the fuselage forebody and wing leading edge extension of the F/A-18 High Alpha Research Vehicle at large incidence. The resulting flows are complex, and exhibit crossflow separation from the sides of the forebody and from the leading edge extension. A well-defined vortex pattern is observed in the leeward-side flow. Results obtained for laminar flow show good agreement with flow visualizations obtained in ground-based experiments. Further, turbulent flows computed at high-Reynolds-number flight-test conditions (M∞ = 0.2, α = 30 °, and Rec = 11.52 × 106) show good agreement with surface and off-surface visualizations obtained in flight.

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Citation Information
Lewis B. Schiff, Russell M. Cummings, Reese L. Sorenson and Yehia M. Rizk. "Numerical Simulation of F-18 Fuselage Forebody Flows at High Angles of Attack" Proceedings of the NASA CFD Conference (1989) p. 345 - 360
Available at: http://works.bepress.com/rcumming/26/