XFOIL Version 6.96 Calculated polar for: GM15 (smoothed) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.750 -0.3535 0.09956 0.09621 -0.0283 1.0000 0.0359 -7.500 -0.3635 0.09830 0.09503 -0.0262 1.0000 0.0360 -7.250 -0.3686 0.09644 0.09322 -0.0254 1.0000 0.0361 -7.000 -0.3701 0.09412 0.09096 -0.0255 1.0000 0.0362 -6.750 -0.3699 0.09154 0.08841 -0.0262 1.0000 0.0362 -6.500 -0.3764 0.08628 0.08322 -0.0219 1.0000 0.0376 -6.250 -0.3737 0.08426 0.08122 -0.0190 1.0000 0.0389 -6.000 -0.3716 0.08237 0.07936 -0.0176 1.0000 0.0412 -5.750 -0.3696 0.07996 0.07698 -0.0181 1.0000 0.0429 -5.500 -0.3644 0.07712 0.07417 -0.0205 1.0000 0.0455 -5.250 -0.3343 0.07237 0.06938 -0.0355 1.0000 0.0484 -5.000 -0.3138 0.06568 0.06267 -0.0425 0.9989 0.0494 -4.750 -0.2943 0.06280 0.05980 -0.0420 0.9955 0.0512 -4.500 -0.2606 0.05920 0.05616 -0.0472 0.9912 0.0544 -4.250 -0.1850 0.04861 0.04525 -0.0708 0.9878 0.0632 -4.000 -0.1570 0.04667 0.04331 -0.0720 0.9836 0.0659 -3.750 -0.0957 0.03882 0.03508 -0.0867 0.9803 0.0775 -3.500 -0.0228 0.02377 0.01823 -0.1000 0.9825 0.0353 -3.250 0.0181 0.02046 0.01428 -0.1031 0.9798 0.0347 -3.000 0.0585 0.01824 0.01155 -0.1058 0.9770 0.0386 -2.750 0.0990 0.01680 0.00988 -0.1082 0.9740 0.0410 -2.500 0.1347 0.01572 0.00863 -0.1094 0.9682 0.0456 -2.250 0.1753 0.01470 0.00756 -0.1119 0.9643 0.0563 -2.000 0.2162 0.01383 0.00672 -0.1144 0.9603 0.0868 -1.750 0.2526 0.01314 0.00644 -0.1162 0.9536 0.2054 -1.500 0.2963 0.01303 0.00632 -0.1193 0.9495 0.2574 -1.250 0.3321 0.01295 0.00626 -0.1208 0.9419 0.2923 -1.000 0.3751 0.01274 0.00604 -0.1236 0.9373 0.3251 -0.750 0.4165 0.01246 0.00578 -0.1261 0.9320 0.3518 -0.500 0.4558 0.01216 0.00555 -0.1282 0.9251 0.3774 -0.250 0.5006 0.01178 0.00523 -0.1313 0.9211 0.4065 0.000 0.5318 0.01151 0.00505 -0.1316 0.9103 0.4330 0.250 0.5648 0.01119 0.00483 -0.1323 0.9002 0.4648 0.500 0.5993 0.01078 0.00458 -0.1332 0.8906 0.5059 0.750 0.6309 0.01025 0.00434 -0.1335 0.8797 0.5794 1.000 0.6678 0.00930 0.00406 -0.1347 0.8667 1.0000 1.250 0.6972 0.00921 0.00387 -0.1345 0.8511 1.0000 1.500 0.7250 0.00916 0.00374 -0.1340 0.8327 1.0000 1.750 0.7541 0.00912 0.00361 -0.1337 0.8140 1.0000 2.000 0.7825 0.00914 0.00356 -0.1334 0.7936 1.0000 2.250 0.8103 0.00921 0.00353 -0.1329 0.7719 1.0000 2.500 0.8370 0.00935 0.00356 -0.1323 0.7494 1.0000 2.750 0.8637 0.00953 0.00363 -0.1316 0.7276 1.0000 3.000 0.8889 0.00975 0.00380 -0.1308 0.7048 1.0000 3.250 0.9143 0.01000 0.00396 -0.1300 0.6835 1.0000 3.500 0.9390 0.01026 0.00416 -0.1291 0.6616 1.0000 3.750 0.9636 0.01054 0.00438 -0.1282 0.6408 1.0000 4.000 0.9879 0.01082 0.00463 -0.1272 0.6195 1.0000 4.250 1.0121 0.01112 0.00494 -0.1263 0.5984 1.0000 4.500 1.0359 0.01143 0.00523 -0.1253 0.5766 1.0000 4.750 1.0587 0.01173 0.00551 -0.1240 0.5507 1.0000 5.000 1.0786 0.01206 0.00570 -0.1221 0.5097 1.0000 5.250 1.0975 0.01249 0.00594 -0.1202 0.4622 1.0000 5.500 1.1174 0.01296 0.00627 -0.1186 0.4186 1.0000 5.750 1.1365 0.01353 0.00672 -0.1169 0.3680 1.0000 6.000 1.1526 0.01441 0.00726 -0.1147 0.2945 1.0000 6.250 1.1529 0.01727 0.00869 -0.1108 0.0847 1.0000 6.500 1.1653 0.01913 0.01032 -0.1081 0.0474 1.0000 6.750 1.1800 0.02058 0.01185 -0.1057 0.0406 1.0000 7.000 1.1959 0.02182 0.01320 -0.1035 0.0367 1.0000 7.250 1.2089 0.02342 0.01482 -0.1011 0.0327 1.0000 7.500 1.2228 0.02533 0.01684 -0.0987 0.0304 1.0000 7.750 1.2416 0.02694 0.01857 -0.0970 0.0290 1.0000 8.000 1.2624 0.02890 0.02065 -0.0956 0.0277 1.0000 8.250 1.2829 0.03064 0.02252 -0.0943 0.0255 1.0000 8.500 1.3018 0.03268 0.02460 -0.0932 0.0231 1.0000 8.750 1.3251 0.03638 0.02852 -0.0925 0.0223 1.0000 9.000 1.3449 0.04002 0.03248 -0.0912 0.0222 1.0000 9.250 1.3610 0.04294 0.03575 -0.0892 0.0225 1.0000 9.500 1.3690 0.04756 0.04124 -0.0850 0.0257 1.0000 9.750 1.3688 0.05407 0.04828 -0.0816 0.0293 1.0000