Aileron effectiveness for a subsonc energy efficient transport (EET) model with a high aspect ratio supercritical wing was determined in the 8-foot transonic pressure tunnel. Data are presented for ailerons located at three positions along the wing span. The ailerons were designed as a preliminary active control concept with gust load alleviation, maneuver load alleviation, and flutter suppression systems. A linear variation of rolling moment coefficient with angle of attack for individual and multiple aileron deflections at Mach numbers up to 0.81 is indicated. For Mach numbers greater than 0.81, the rolling moment coefficient data become nonlinear with increasing angle of attack. At Mach numbers near the design value increased aileron effectiveness resulted from aft transition locations, which produced relatively thin boundary layers and greater effective aileron deflections. Individual aileron deflections on the right wing panel produced only small effects on yawing moment and side force coefficients.
Aileron Effectiveness for a Subsonic Transport Model with a High-Aspect-Ratio Supercritical Wing
1983
277 pages
Report
No indication
English
Aerodynamics , Aerodynamic characteristics , Ailerons , Dynamic control , High aspect ratio , Lateral stability , Subsonic speed , Supercritical wings , Wind tunnel tests , Angle of attack , Boundary layer separation , Mach number , Rolling moments , Slender wings , Transport aircraft , Wing profiles
Engineering Index Backfile | 1954
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