Title

Numerical Simulation of F-18 Fuselage Forebody Flows at High Angles of Attack

Author Info

Lewis B. Schiff, NASA Ames Research Center
Russell M. Cummings, NASA Ames Research CenterFollow
Reese L. Sorenson, NASA Ames Research Center
Yehia M. Rizk, NASA Ames Research Center

Recommended Citation

Published in Proceedings of the NASA CFD Conference, March 1, 1989, pages 345-360.

NOTE: At the time of publication, the author Russell M. Cummings was not yet affiliated with Cal Poly.

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 Re_c = 11.52 × 106) show good agreement with surface and off-surface visualizations obtained in flight.

Disciplines

Aerospace Engineering

Copyright

This article is in the public domain.