XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0406 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.6684 0.10426 0.09922 0.0124 1.0000 0.0335 -9.250 -0.6720 0.09797 0.09300 0.0083 1.0000 0.0304 -9.000 -0.6755 0.09001 0.08507 0.0011 1.0000 0.0266 -8.750 -0.6763 0.08498 0.08008 -0.0020 1.0000 0.0261 -8.500 -0.6779 0.07893 0.07404 -0.0079 1.0000 0.0257 -8.250 -0.6771 0.07279 0.06784 -0.0134 1.0000 0.0252 -8.000 -0.6746 0.06683 0.06175 -0.0178 1.0000 0.0247 -7.750 -0.6692 0.06092 0.05566 -0.0214 1.0000 0.0242 -7.500 -0.6605 0.05509 0.04955 -0.0243 1.0000 0.0237 -7.250 -0.6480 0.04943 0.04353 -0.0266 1.0000 0.0233 -7.000 -0.6317 0.04408 0.03774 -0.0283 1.0000 0.0229 -6.750 -0.6121 0.03912 0.03225 -0.0295 1.0000 0.0227 -6.500 -0.5895 0.03470 0.02726 -0.0304 1.0000 0.0226 -6.250 -0.5648 0.03093 0.02290 -0.0309 1.0000 0.0229 -6.000 -0.5387 0.02778 0.01921 -0.0311 1.0000 0.0235 -5.750 -0.5120 0.02521 0.01618 -0.0310 1.0000 0.0246 -5.500 -0.4848 0.02367 0.01414 -0.0308 1.0000 0.0274 -5.250 -0.4593 0.02163 0.01203 -0.0308 1.0000 0.0304 -5.000 -0.4330 0.02009 0.01036 -0.0306 1.0000 0.0331 -4.750 -0.4065 0.01867 0.00879 -0.0302 1.0000 0.0373 -4.500 -0.3801 0.01741 0.00751 -0.0302 1.0000 0.0452 -4.250 -0.3533 0.01671 0.00678 -0.0303 1.0000 0.0631 -4.000 -0.3262 0.01578 0.00576 -0.0303 1.0000 0.0793 -3.750 -0.2990 0.01495 0.00500 -0.0306 1.0000 0.1045 -3.500 -0.2715 0.01403 0.00432 -0.0309 1.0000 0.1516 -3.250 -0.2453 0.01224 0.00380 -0.0319 1.0000 0.4108 -3.000 -0.2230 0.01158 0.00384 -0.0305 1.0000 0.6034 -2.750 -0.2007 0.01142 0.00381 -0.0287 1.0000 0.6838 -2.500 -0.1790 0.01135 0.00382 -0.0267 1.0000 0.7375 -2.250 -0.1599 0.01132 0.00385 -0.0241 1.0000 0.7841 -2.000 -0.1431 0.01128 0.00387 -0.0208 1.0000 0.8247 -1.750 -0.1266 0.01119 0.00381 -0.0176 1.0000 0.8570 -1.500 -0.1067 0.01106 0.00364 -0.0156 1.0000 0.8795 -1.250 -0.0847 0.01091 0.00346 -0.0142 1.0000 0.8971 -1.000 -0.0615 0.01076 0.00330 -0.0132 1.0000 0.9152 -0.750 -0.0371 0.01060 0.00314 -0.0125 1.0000 0.9340 -0.500 -0.0090 0.01047 0.00301 -0.0127 1.0000 0.9553 -0.250 0.0212 0.01035 0.00291 -0.0136 1.0000 0.9874 0.000 0.0478 0.01034 0.00291 -0.0140 1.0000 1.0000 0.250 0.0764 0.01040 0.00298 -0.0148 1.0000 1.0000 0.500 0.1049 0.01049 0.00311 -0.0155 1.0000 1.0000 0.750 0.1332 0.01061 0.00328 -0.0162 1.0000 1.0000 1.000 0.1612 0.01075 0.00350 -0.0168 1.0000 1.0000 1.250 0.1891 0.01091 0.00376 -0.0174 1.0000 1.0000 1.500 0.2530 0.01088 0.00396 -0.0247 0.9693 1.0000 1.750 0.3084 0.01069 0.00393 -0.0292 0.9015 1.0000 2.000 0.3461 0.01073 0.00385 -0.0296 0.7817 1.0000 2.250 0.3662 0.01177 0.00377 -0.0264 0.5002 1.0000 2.500 0.3877 0.01355 0.00430 -0.0259 0.2176 1.0000 2.750 0.4132 0.01473 0.00493 -0.0260 0.1159 1.0000 3.000 0.4401 0.01561 0.00570 -0.0259 0.0877 1.0000 3.250 0.4670 0.01647 0.00655 -0.0258 0.0667 1.0000 3.500 0.4936 0.01734 0.00739 -0.0258 0.0484 1.0000 3.750 0.5203 0.01830 0.00843 -0.0257 0.0367 1.0000 4.000 0.5462 0.01973 0.00993 -0.0254 0.0318 1.0000 4.250 0.5731 0.02128 0.01167 -0.0250 0.0291 1.0000 4.500 0.6002 0.02303 0.01362 -0.0246 0.0273 1.0000 4.750 0.6271 0.02500 0.01587 -0.0243 0.0261 1.0000 5.000 0.6536 0.02728 0.01849 -0.0239 0.0253 1.0000 5.250 0.6789 0.02995 0.02163 -0.0235 0.0248 1.0000 5.500 0.7025 0.03297 0.02509 -0.0231 0.0242 1.0000 5.750 0.7227 0.03687 0.02947 -0.0228 0.0229 1.0000 6.000 0.7440 0.04058 0.03387 -0.0221 0.0216 1.0000 6.250 0.7613 0.04529 0.03912 -0.0217 0.0213 1.0000 6.500 0.7758 0.05036 0.04464 -0.0217 0.0214 1.0000 6.750 0.7876 0.05565 0.05031 -0.0220 0.0216 1.0000 7.000 0.7965 0.06108 0.05604 -0.0227 0.0218 1.0000 7.250 0.8027 0.06656 0.06175 -0.0238 0.0221 1.0000 7.500 0.8060 0.07208 0.06745 -0.0254 0.0224 1.0000 7.750 0.8067 0.07754 0.07304 -0.0273 0.0227 1.0000 8.000 0.8047 0.08280 0.07835 -0.0289 0.0231 1.0000 8.500 0.7936 0.10012 0.09578 -0.0462 0.0270 1.0000 8.750 0.7900 0.10615 0.10177 -0.0502 0.0284 1.0000 9.000 0.7886 0.11152 0.10711 -0.0531 0.0299 1.0000 9.250 0.7893 0.11628 0.11184 -0.0545 0.0319 1.0000 9.500 0.6483 0.11096 0.10670 -0.0399 0.0286 1.0000 9.750 0.6448 0.11578 0.11149 -0.0413 0.0298 1.0000