Aerodynamic Analysis of a Fighter Aircraft with a Higher Order Paneling Method
Final rept. Sep 1978-Jan 1981
BOEING MILITARY AIRPLANE CO SEATTLE WA
Pagination or Media Count:
This report presents results from analyses of steady and unsteady flows about several configurations involving the wing of the F-5 fighter airplane. The analyses were performed using higher order panel methods and the configurations analyzed included the following the clean wing both in an unbounded and in a wind tunnel wall bounded atmosphere, the wing with an external missile store mounted at the wing tip, and the wing with an external missile store mounted on a pylon at the lower surface of the wing. The flow mach number ranged from 0.6 to 1.35 in steady flow and from 0.6 to 0.95 in unsteady flow. Each steady flow case is analyzed at three angles of attack 0.5 deg, 0.0 deg, 0.5 deg while each unsteady flow case consisted of unsteady pitch oscillation about zero angle of attack. The reduced frequency of the oscillation was in the range from 0.2498 to 0.3955. The computed results include chordwise pressure distributions along wing sections at eight spanwise locations from 18.1 to 97.7 per cent semispan. The results also include the coefficients of lift and pitching moment for each complete configuration as well as the coefficients of aerodynamic force and couple arising from the pressure on only the surface of the missile store.
- Attack and Fighter Aircraft