Control-Surface Deflection Effects on the Innovative Control Effectors (ICE 101) Design

摘要

A static wind tunnel test of the Innovative Controls Effectors (ICE 101) conceptual aircraft configuration was conducted in the Air Force Research Laboratory's Vertical Wind Tunnel. This entry characterized the increments to the aerodynamic loading provided by the various control surfaces while using a more finely-resolved test matrix in angle of attack and sideslip than typically seen in wind tunnel testing. The purpose for obtaining these data was to determine the effect which control surface deflection had on critical state locations in preparation for the test of a second ICE model built with remotely- actuated control surfaces. (Critical states are discrete flight mechanical states where the aerodynamic response looses its analytic dependence on one or more state variables.) These data demonstrate that the aerodynamic increments are in many cases at minimum nonlinear functions of the surface deflection angle, and strongly suggest that some critical states do shift in angle of attack and/or sideslip with changing deflection angle.