Leading-edge slat optimization for maximum airfoil liftNational Aeronautics and Space Administration, Scientific and Technical Information Office, 1979 - Aerfoils - 23 pages |
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Page 18
... xg / c = −0.01 , yg / c = 0.01 , −0.01 , ys / c = 0.01 , dƒ = 10 ° , Re 3.8X106 . -118 -10 -9 PRESSURE COEFFICIENT , Cp -5 -4 -3 18.
... xg / c = −0.01 , yg / c = 0.01 , −0.01 , ys / c = 0.01 , dƒ = 10 ° , Re 3.8X106 . -118 -10 -9 PRESSURE COEFFICIENT , Cp -5 -4 -3 18.
Page 19
... c = 10 ° , Figure 7.- Comparison of theoretical and experimental pressure distributions near stall with a section lift coefficient of 3.1 : ds : -42 ° , xg / c = -0.01 , ys / c = 0.02 , s Re = 3.88106 . = MAXIMUM LIFT COEFFICIENT ...
... c = 10 ° , Figure 7.- Comparison of theoretical and experimental pressure distributions near stall with a section lift coefficient of 3.1 : ds : -42 ° , xg / c = -0.01 , ys / c = 0.02 , s Re = 3.88106 . = MAXIMUM LIFT COEFFICIENT ...
Page 20
... c = -0.007 2.9 -.02 -.01 0 SLAT HORIZONTAL LOCATION , xg / c Figure 8.- Effect of slat trailing - edge horizontal location on wing maximum lift : 8 ys / c = 0.01 , 8 бр = 10 ° , Re 3.8X106 . = = -40 ° , S 3.3 3.2 A MAXIMUM LIFT ...
... c = -0.007 2.9 -.02 -.01 0 SLAT HORIZONTAL LOCATION , xg / c Figure 8.- Effect of slat trailing - edge horizontal location on wing maximum lift : 8 ys / c = 0.01 , 8 бр = 10 ° , Re 3.8X106 . = = -40 ° , S 3.3 3.2 A MAXIMUM LIFT ...
Common terms and phrases
80-Foot Wind Tunnel adverse pressure gradient aerodynamic analysis aerodynamic calculation Ames 40 Ames Research Center angle of attack attached flow boundary-layer coordinate system boundary-layer equations Cebeci CLMAX Computer Sciences Corporation configurations confluent boundary layer constrained function minimization constraint coupling potential flow determining the position eddy viscosity experimentally optimized slat finite-difference flow field high-lift horizontal location incipient flow separation iteratively coupling potential laminar instability LEADING-EDGE SLAT OPTIMIZATION main airfoil main element MAXIMUM AIRFOIL LIFT MAXIMUM LIFT COEFFICIENT measured maximum lift minimizes the suction Moffett Field multielement airfoils NASA OPTIMIZATION FOR MAXIMUM optimized slat position position for maximum position that minimizes pressure distributions Reynolds number Reynolds stress single-slotted flap skin friction slat deflection slat horizontal SLAT LOCATION slat vertical slat wake suction peak Swept Wings THEORETICAL METHOD theoretical predictions theoretically optimized trailing edge trailing-edge Vanderplaats vertical location wind-tunnel testing wing maximum lift xg/c xs/c Ys/c ફ્