Experimental and Theoretical Aerodynamic Characteristics of a High-Lift Semispan Wing Model PDF Download

Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723047640
Category :
Languages : en
Pages : 114

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Book Description
Experimental and theoretical aerodynamic characteristics were compared for a high-lift, semispan wing configuration that incorporated a slightly modified version of the NASA Advanced Laminar Flow Control airfoil section. The experimental investigation was conducted in the Langley 14- by 22-Foot Subsonic Tunnel at chord Reynolds numbers of 2.36 and 3.33 million. A two-dimensional airfoil code and a three-dimensional panel code were used to obtain aerodynamic predictions. Two-dimensional data were corrected for three-dimensional effects. Comparisons between predicted and measured values were made for the cruise configuration and for various high-lift configurations. Both codes predicted lift and pitching moment coefficients that agreed well with experiment for the cruise configuration. These parameters were overpredicted for all high-lift configurations. Drag coefficient was underpredicted for all cases. Corrected two-dimensional pressure distributions typically agreed well with experiment, while the panel code overpredicted the leading-edge suction peak on the wing. One important feature missing from both of these codes was a capability for separated flow analysis. The major cause of disparity between the measured data and predictions presented herein was attributed to separated flow conditions. Applin, Zachary T. and Gentry, Garl L., Jr. Langley Research Center AERODYNAMIC CHARACTERISTICS; AERODYNAMIC CONFIGURATIONS; AIRFOIL PROFILES; BOUNDARY LAYER CONTROL; COMPUTER PROGRAMS; LAMINAR BOUNDARY LAYER; PANEL METHOD (FLUID DYNAMICS); SEMISPAN MODELS; AERODYNAMIC DRAG; LEADING EDGES; LIFT; MOMENT DISTRIBUTION; PRESSURE DISTRIBUTION; REYNOLDS NUMBER; SEPARATED FLOW; SUBSONIC WIND TUNNELS...