INVESTIGATION AND MODIFICATION OF AERODYNAMIC CHARACTERISTICS OF SUPERSONIC AIRCRAFT

Abstract

Increasing the aerodynamic efficiency and enhancing the supermaneuverability for the selected supersonic aircraft (F-16A) is presented. Aerodynamic characteristics, surface pressure distribution and maximum lift are are estimated for the baseline configuration for different Mach number and angles of attack in subsonic and supersonic potential flow, using a low order three- dimensional panel method supported with semi-empirical formulas of Datcom.

Estimation of the total nose-up and nose-down pitching moments about the center of gravity of the completed aircraft in subsonic region depending on the flight conditions and aircraft performance limitations. A modern program was implemented by suggesting a two dimensional thrust vectoring technique (pitch vectoring up and down) controlled by the best design of advanced aerodynamic and control surface (foreplane or canard). Work results shows that the canard (as a control surface) with thrust vectoring produces enough nose-down moment and can support the stabilator at high maneuvers, while for an aerodynamic surface, a rate of (5-6%) increase was achieved in the aerodynamic efficiency (lift-to-drag ratio) of the baseline configuration in both subsonic and supersonic flight