An experimental and numerical investigation of high alpha aerodynamics is reported for a generic compound delta wing fighter aircraft configuration in transonic Mach number regime. The aircraft considered here is a wing-fuselage-vertical fin tailless compound delta configuration with lower inboard and higher outboard sweeps and a close combat missile outboard. The basic configuration does not have any leading or trailing edge devices such as slats and flaps. This configuration is studied first to understand the flow physics causing pitch up phenomenon for the basic configuration. Subsequently, the use of leading edge vortex controller (LEVCON) is studied for controlling pitch up. Both Computational Fluid Dynamics (CFD) and wind tunnel experiments have been used to describe the flow physics. Copyright © 2008 by American Institute of Aeronautics and Astronautics, Inc.