2018/3/11 Supersonic Lift-Curve Slope 国上唐美大坐 Transonic Lift-Curve Slope 国上清大学 ·For“pure”supersonic wings(Mo>l) 8a2提 THEDRO TICAL La=41B 5,"m- where,B=M-1 M>1/COsALE Curve fitting is SICI AL BCT RATIO WIMA often used for the a =aresin(1/M) cases oftransonic flight regime OW ASPECT RAT For real,nontrapezoidal wing planforms, approximate charts and panel methods are usually used (Raymer,pp.314-315) 15 5 Erfect of Ma,Sweep()on CLmax()圈上活支道大坐 Effect of Leading Edge Radius on CLmax 园上活道大整 For subsonic wing (Ma<0.8) CLmas=0.9C1mxco个025 Low aspect ratio High aspect ratio 3 4 C.+lcosA 16 45C.+IXcOsAu) -o C-CAC. Use of leading edge sharpness _C+a+小e parameters Ay to characterize eratsad Shaded items are defined using a number ofcharts in Chapter 12.pp317-321. Design of High-Lift Devices 国上洋大坐 Lift in Summary 园上海发大坐 Use of lift coefficients in the aerodynamic design process Setting wing incidence angle C Caleulation of drag-due-to-lift Analysis of longitudinal stability CLma Takeoff weight △CLm=0.9AC D Range Aau=(△au) slty-Dr.V(enbin Song 32018/3/11 3 © Shanghai Jiao Tong University – Dr. Wenbin Song School of Aeronautics and Astronautics Supersonic Lift-Curve Slope • CL  4 /  1 2   M  α =arcsin(1/M) ΛLE M  LE 1/ cos © Shanghai Jiao Tong University – Dr. Wenbin Song School of Aeronautics and Astronautics Transonic Lift-Curve Slope Curve fitting is often used for the cases of transonic flight regime © Shanghai Jiao Tong University – Dr. Wenbin Song School of Aeronautics and Astronautics Effect of Ma, Sweep(Λ) on CLmax (I) • For subsonic wing (Ma<0.8) CLmax Cl max 0.25c  0.9 cos    C LE A    1 cos 3 1    C LE A    1 cos 3 1 Low aspect ratio High aspect ratio CLmax αCLmax max max max max max L l L L l C C C C C            max max 0 max L L CL L L C C C           CLmax  CLmax base  CLmax   CL max CL max base CLmax      Shaded items are defined using a number of charts in Chapter 12, pp 317-321. © Shanghai Jiao Tong University – Dr. Wenbin Song School of Aeronautics and Astronautics Effect of Leading Edge Radius on CLmax Use of leading edge sharpness parameters Δy to characterize the leading edge radius and airfoil camber © Shanghai Jiao Tong University – Dr. Wenbin Song School of Aeronautics and Astronautics Design of High-Lift Devices HL ref flapped L l S S C C            0.9 cos max max   HL ref flapped L L airfoil S S             cos 0 0 © Shanghai Jiao Tong University – Dr. Wenbin Song School of Aeronautics and Astronautics Lift in Summary CL CLmax max       D L Wing area Skin friction drag Takeoff weight Range Setting wing incidence angle Calculation of drag-due-to-lift Analysis of longitudinal stability Use of lift coefficients in the aerodynamic design process