Investigation of a Double Slotted Rudder for Application on Advanced Tactical Transport Aircraft.

摘要

The aerodynamic and mechanical design of a double slotted rudder (DSR) system for possible use on the next generation STOL transport aircraft has been synthesized and the aerodynamic configuration tested in the Wichita State University low speed wind tunnel. Data collected during the Phase I wind tunnel program shows the double slotted rudder in combination with a typical transport aircraft vertical tail produces sixty per cent greater side force than a comparable double hinged rudder design. Adjustment in slotted rudder geometry directed toward actuation mechanism simplification were made and tested in the second phase of the program. The changes investigated had minimal impact on slotted rudder aerodynamic performance. Further design analysis of the mechanically simplified DSR configuration and wind tunnel testing of a completely operable double slotted rudder are recommended before making a final assessment of the concept. (Author)