XFOIL Version 6.96 Calculated polar for: EPPLER 336 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.4168 0.09207 0.08932 -0.0225 0.6518 0.0066 -8.500 -0.4996 0.06351 0.06054 -0.0316 0.5982 0.0063 -7.000 -0.5750 0.02597 0.02111 -0.0037 0.5626 0.0037 -6.750 -0.5657 0.02233 0.01696 -0.0003 0.5533 0.0036 -6.500 -0.5496 0.01975 0.01395 0.0020 0.5426 0.0036 -6.250 -0.5284 0.01821 0.01214 0.0033 0.5331 0.0035 -6.000 -0.5056 0.01688 0.01055 0.0044 0.5244 0.0035 -5.750 -0.4814 0.01597 0.00947 0.0052 0.5148 0.0035 -5.500 -0.4570 0.01508 0.00840 0.0060 0.5063 0.0035 -5.250 -0.4323 0.01435 0.00753 0.0067 0.4979 0.0035 -5.000 -0.4076 0.01371 0.00676 0.0074 0.4903 0.0035 -4.750 -0.3830 0.01315 0.00610 0.0081 0.4825 0.0035 -4.500 -0.3586 0.01266 0.00552 0.0089 0.4753 0.0036 -4.250 -0.3338 0.01228 0.00506 0.0096 0.4678 0.0036 -4.000 -0.3094 0.01189 0.00459 0.0104 0.4607 0.0036 -3.750 -0.2847 0.01156 0.00420 0.0111 0.4539 0.0036 -3.500 -0.2600 0.01127 0.00385 0.0118 0.4470 0.0037 -3.250 -0.2349 0.01101 0.00354 0.0124 0.4409 0.0037 -3.000 -0.2098 0.01078 0.00327 0.0131 0.4341 0.0038 -2.750 -0.1852 0.01052 0.00294 0.0138 0.4281 0.0040 -2.500 -0.1597 0.01033 0.00273 0.0144 0.4217 0.0044 -2.250 -0.1341 0.01020 0.00255 0.0149 0.4150 0.0047 -2.000 -0.1082 0.01008 0.00239 0.0154 0.4082 0.0056 -1.750 -0.0825 0.00996 0.00225 0.0159 0.3997 0.0069 -1.500 -0.0567 0.00986 0.00213 0.0164 0.3926 0.0098 -1.250 -0.0311 0.00975 0.00202 0.0169 0.3840 0.0179 -1.000 -0.0058 0.00961 0.00193 0.0174 0.3763 0.0354 -0.750 0.0184 0.00943 0.00185 0.0181 0.3664 0.0766 -0.500 0.0412 0.00915 0.00178 0.0190 0.3569 0.1517 -0.250 0.0251 0.00691 0.00140 0.0273 0.3523 0.6870 0.000 0.0342 0.00652 0.00168 0.0319 0.3471 0.8743 0.250 0.0603 0.00667 0.00179 0.0325 0.3420 0.8881 0.500 0.0857 0.00685 0.00191 0.0332 0.3383 0.8986 0.750 0.1139 0.00703 0.00207 0.0334 0.3356 0.9049 1.000 0.1410 0.00720 0.00221 0.0338 0.3328 0.9108 1.250 0.1666 0.00732 0.00229 0.0344 0.3300 0.9155 1.500 0.1946 0.00737 0.00230 0.0344 0.3277 0.9166 1.750 0.2225 0.00742 0.00231 0.0344 0.3256 0.9173 2.000 0.2503 0.00748 0.00233 0.0343 0.3230 0.9180 2.250 0.2784 0.00753 0.00235 0.0343 0.3214 0.9187 2.500 0.3064 0.00757 0.00237 0.0342 0.3198 0.9194 2.750 0.3343 0.00761 0.00240 0.0341 0.3183 0.9200 3.000 0.3621 0.00766 0.00243 0.0341 0.3166 0.9206 3.250 0.3897 0.00771 0.00247 0.0340 0.3145 0.9213 3.500 0.4172 0.00778 0.00252 0.0340 0.3123 0.9221 3.750 0.4446 0.00785 0.00258 0.0340 0.3103 0.9229 4.000 0.4717 0.00795 0.00265 0.0340 0.3076 0.9237 4.250 0.4992 0.00800 0.00270 0.0340 0.3060 0.9244 4.500 0.5270 0.00804 0.00276 0.0339 0.3045 0.9250 4.750 0.5547 0.00809 0.00281 0.0338 0.3024 0.9257 5.000 0.5822 0.00815 0.00287 0.0337 0.2999 0.9264 5.250 0.6094 0.00822 0.00294 0.0337 0.2968 0.9270 5.500 0.6365 0.00831 0.00303 0.0337 0.2938 0.9277 5.750 0.6635 0.00840 0.00312 0.0336 0.2909 0.9284 6.000 0.6911 0.00846 0.00320 0.0335 0.2886 0.9290 6.250 0.7184 0.00852 0.00328 0.0334 0.2846 0.9297 6.500 0.7454 0.00861 0.00337 0.0334 0.2800 0.9303 6.750 0.7724 0.00870 0.00346 0.0334 0.2755 0.9309 7.000 0.7994 0.00878 0.00356 0.0333 0.2686 0.9316 7.250 0.8258 0.00891 0.00367 0.0334 0.2600 0.9323 7.500 0.8516 0.00907 0.00381 0.0335 0.2507 0.9330 7.750 0.8774 0.00923 0.00397 0.0336 0.2432 0.9337 8.000 0.9023 0.00944 0.00416 0.0338 0.2347 0.9345 8.250 0.9275 0.00962 0.00435 0.0340 0.2271 0.9353 8.500 0.9520 0.00985 0.00457 0.0343 0.2190 0.9361 8.750 0.9761 0.01009 0.00480 0.0347 0.2096 0.9370 9.000 0.9999 0.01035 0.00505 0.0351 0.1990 0.9380 9.250 1.0227 0.01066 0.00533 0.0356 0.1871 0.9391 9.500 1.0448 0.01100 0.00564 0.0362 0.1750 0.9402 9.750 1.0659 0.01138 0.00598 0.0370 0.1620 0.9416 10.000 1.0858 0.01181 0.00636 0.0379 0.1483 0.9430 10.250 1.1056 0.01223 0.00675 0.0388 0.1368 0.9443 10.750 1.1412 0.01319 0.00765 0.0413 0.1122 0.9473 11.000 1.1565 0.01373 0.00815 0.0429 0.1002 0.9492 11.250 1.1701 0.01429 0.00869 0.0447 0.0890 0.9515 11.500 1.1822 0.01479 0.00919 0.0469 0.0810 0.9541 11.750 1.1916 0.01529 0.00970 0.0495 0.0743 0.9575 12.000 1.1974 0.01598 0.01038 0.0525 0.0657 0.9614 12.250 1.2069 0.01668 0.01110 0.0545 0.0599 0.9658 12.500 1.2160 0.01751 0.01195 0.0562 0.0532 0.9713 12.750 1.2294 0.01861 0.01307 0.0564 0.0467 0.9761 13.000 1.2444 0.01999 0.01447 0.0555 0.0407 0.9806 13.250 1.2603 0.02145 0.01597 0.0542 0.0361 0.9846 13.500 1.2756 0.02332 0.01789 0.0521 0.0315 0.9873 13.750 1.2884 0.02553 0.02014 0.0498 0.0278 0.9901 14.000 1.2998 0.02778 0.02245 0.0478 0.0250 0.9940 14.250 1.2997 0.03040 0.02512 0.0474 0.0228 1.0000 14.500 1.2960 0.03301 0.02779 0.0476 0.0208 1.0000 14.750 1.2924 0.03574 0.03059 0.0476 0.0198 1.0000 15.000 1.2842 0.03904 0.03395 0.0473 0.0178 1.0000 15.250 1.2760 0.04240 0.03737 0.0470 0.0161 1.0000 15.500 1.2671 0.04592 0.04097 0.0465 0.0151 1.0000 15.750 1.2565 0.04968 0.04479 0.0459 0.0133 1.0000 16.000 1.2531 0.05273 0.04793 0.0453 0.0140 1.0000 16.250 1.2484 0.05600 0.05130 0.0446 0.0144 1.0000 16.750 1.2267 0.06434 0.05976 0.0425 0.0117 1.0000 17.000 1.2180 0.06834 0.06383 0.0414 0.0108 1.0000 17.250 1.2051 0.07300 0.06853 0.0400 0.0093 1.0000 17.500 1.1979 0.07698 0.07258 0.0387 0.0087 1.0000 17.750 1.1934 0.08065 0.07634 0.0376 0.0092 1.0000 18.000 1.1843 0.08498 0.08073 0.0361 0.0080 1.0000 18.250 1.1765 0.08918 0.08499 0.0347 0.0075 1.0000