Multi-element airfoil optimization for maximum lift at high Reynolds numbersAn experimental study has been performed to assess the maximum lift capability of a supercritical multielement airfoil representative of an advanced transport aircraft wing. The airfoil model was designed with a leading-edge slat and single or two-segment trailing-edge flaps. Optimization work was performed at various slat/flap deflections as well as gap/overhang positions. Landing configurations and the attainment of maximum lift coefficients of 4.5 with single-element flaps and 5.0 with two-segment flaps was emphasized. Test results showed a relatively linear variation of the optimum gap/overhang positioning of the slat versus slat deflection, considerable differences in optimum rigging between single and double segment flaps, and large Reynolds number effects on multielement airfoil optimization.
Valarezo, Walter O. (Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Dominik, Chet J. (Douglas Aircraft Co. Long Beach, CA, United States)
Mcghee, Robert J. (Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Goodman, Wesley L. (Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Paschal, Keith B. (NASA Langley Research Center Hampton, VA, United States)