STOE Potential of the Circulation Control Wing for High-Performance Aircraft

Abstract

Research and development being conducted at the David Taylor Naval Ship R and D Center investigates the STOL capability of the Circulation Control Wing (CCW) concept on high-performa nce aircraft. This high-lift system, which employs tangential blowing over a rounded trailing edge and requires mass flows characteristic of state-of-the-art turbine engine bleed, has demonstrated the ability to more than double the lift capability of conventional Navy and Marine aircraft. The resulting reduced takeoff and landing speeds and distances, plus increased overload capability, are achieved without severe compromise of wing structure, weight, or engine arrangement, and without large quantities of ducted hot gas. Based on these anticipated benefits and the results of existing experimental investigations, a program has been initiated to demonstrate the STOL capability of the CCW concept applied to a full-scale A-6 flight demonstrator aircraft. This paper will address the experimental development and optimization of the CCW system on an A-6 model and will present predicted full-scale STOL performance gains for the flight demonstrator.