XFOIL Version 6.96 Calculated polar for: RAF 32 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.750 -0.6923 0.09299 0.09079 -0.0699 1.0000 0.0146 -15.500 -0.7401 0.08237 0.08005 -0.0749 1.0000 0.0144 -15.250 -0.7875 0.07306 0.07063 -0.0790 1.0000 0.0144 -15.000 -0.8357 0.06475 0.06221 -0.0820 1.0000 0.0142 -14.750 -0.8654 0.05470 0.05199 -0.0915 0.9983 0.0141 -14.500 -0.8878 0.04391 0.04100 -0.1041 0.9950 0.0141 -14.250 -0.8969 0.03427 0.03113 -0.1176 0.9900 0.0141 -14.000 -0.8862 0.02762 0.02422 -0.1310 0.9846 0.0144 -13.750 -0.8662 0.02544 0.02191 -0.1342 0.9810 0.0147 -13.500 -0.8452 0.02392 0.02029 -0.1359 0.9770 0.0150 -13.250 -0.8186 0.02261 0.01887 -0.1381 0.9748 0.0155 -13.000 -0.7901 0.02138 0.01753 -0.1404 0.9733 0.0159 -12.750 -0.7593 0.02031 0.01634 -0.1426 0.9722 0.0164 -12.500 -0.7263 0.01934 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0.3232 0.00702 0.00152 -0.1412 0.7508 0.1882 -2.250 0.3493 0.00689 0.00147 -0.1408 0.7434 0.2228 -2.000 0.3759 0.00683 0.00144 -0.1405 0.7369 0.2463 -1.750 0.4025 0.00677 0.00142 -0.1402 0.7296 0.2660 -1.500 0.4289 0.00674 0.00140 -0.1399 0.7228 0.2833 -1.250 0.4557 0.00670 0.00139 -0.1396 0.7155 0.2998 -0.750 0.5087 0.00665 0.00138 -0.1390 0.7016 0.3352 -0.500 0.5347 0.00663 0.00138 -0.1386 0.6944 0.3583 -0.250 0.5610 0.00656 0.00140 -0.1383 0.6879 0.3929 0.000 0.5869 0.00651 0.00143 -0.1379 0.6812 0.4301 0.250 0.6126 0.00646 0.00147 -0.1374 0.6751 0.4748 0.500 0.6386 0.00641 0.00153 -0.1371 0.6687 0.5178 0.750 0.6639 0.00640 0.00159 -0.1365 0.6625 0.5631 1.000 0.6902 0.00637 0.00165 -0.1362 0.6571 0.5965 1.250 0.7162 0.00637 0.00171 -0.1357 0.6513 0.6233 1.500 0.7412 0.00640 0.00178 -0.1351 0.6446 0.6523 1.750 0.7666 0.00638 0.00184 -0.1346 0.6376 0.6845 2.000 0.7906 0.00640 0.00192 -0.1337 0.6307 0.7236 2.250 0.8150 0.00633 0.00200 -0.1329 0.6246 0.7722 2.500 0.8359 0.00619 0.00209 -0.1313 0.6179 0.8541 2.750 0.8931 0.00616 0.00222 -0.1379 0.6095 1.0000 3.000 0.9163 0.00629 0.00229 -0.1369 0.5990 1.0000 3.250 0.9409 0.00637 0.00237 -0.1362 0.5895 1.0000 3.500 0.9645 0.00650 0.00245 -0.1353 0.5815 1.0000 3.750 0.9897 0.00658 0.00253 -0.1347 0.5740 1.0000 4.000 1.0129 0.00671 0.00263 -0.1337 0.5641 1.0000 4.250 1.0365 0.00683 0.00273 -0.1328 0.5535 1.0000 4.500 1.0600 0.00696 0.00284 -0.1319 0.5427 1.0000 4.750 1.0822 0.00712 0.00296 -0.1308 0.5299 1.0000 5.000 1.1031 0.00731 0.00309 -0.1294 0.5129 1.0000 5.250 1.1228 0.00753 0.00325 -0.1277 0.4933 1.0000 5.500 1.1396 0.00784 0.00345 -0.1255 0.4683 1.0000 5.750 1.1522 0.00823 0.00369 -0.1225 0.4379 1.0000 6.000 1.1657 0.00863 0.00396 -0.1196 0.4111 1.0000 6.250 1.1796 0.00904 0.00424 -0.1170 0.3826 1.0000 6.500 1.1923 0.00952 0.00457 -0.1141 0.3506 1.0000 6.750 1.2019 0.01014 0.00499 -0.1108 0.3088 1.0000 7.000 1.2074 0.01095 0.00554 -0.1068 0.2598 1.0000 7.250 1.2160 0.01167 0.00606 -0.1035 0.2258 1.0000 7.500 1.2263 0.01234 0.00658 -0.1005 0.1969 1.0000 7.750 1.2367 0.01302 0.00712 -0.0976 0.1682 1.0000 8.000 1.2439 0.01387 0.00778 -0.0943 0.1325 1.0000 8.250 1.2473 0.01494 0.00862 -0.0906 0.0936 1.0000 8.500 1.2563 0.01578 0.00935 -0.0878 0.0750 1.0000 8.750 1.2694 0.01644 0.00997 -0.0857 0.0665 1.0000 9.000 1.2841 0.01704 0.01056 -0.0839 0.0607 1.0000 9.250 1.2981 0.01768 0.01120 -0.0820 0.0562 1.0000 9.500 1.3127 0.01832 0.01184 -0.0803 0.0517 1.0000 9.750 1.3273 0.01897 0.01250 -0.0786 0.0479 1.0000 10.000 1.3403 0.01973 0.01324 -0.0768 0.0434 1.0000 10.250 1.3543 0.02045 0.01396 -0.0752 0.0393 1.0000 10.500 1.3669 0.02128 0.01479 -0.0735 0.0354 1.0000 10.750 1.3796 0.02212 0.01563 -0.0718 0.0325 1.0000 11.000 1.3909 0.02307 0.01659 -0.0700 0.0297 1.0000 11.250 1.4034 0.02397 0.01751 -0.0685 0.0277 1.0000 11.500 1.4129 0.02509 0.01865 -0.0667 0.0256 1.0000 11.750 1.4242 0.02611 0.01971 -0.0651 0.0243 1.0000 12.000 1.4356 0.02715 0.02079 -0.0637 0.0231 1.0000 12.250 1.4453 0.02834 0.02200 -0.0621 0.0220 1.0000 12.500 1.4509 0.02988 0.02358 -0.0603 0.0208 1.0000 12.750 1.4618 0.03104 0.02480 -0.0590 0.0201 1.0000 13.000 1.4717 0.03230 0.02611 -0.0577 0.0195 1.0000 13.250 1.4810 0.03365 0.02751 -0.0564 0.0188 1.0000 13.500 1.4889 0.03513 0.02902 -0.0551 0.0180 1.0000 13.750 1.4925 0.03703 0.03097 -0.0536 0.0173 1.0000 14.000 1.4961 0.03898 0.03300 -0.0522 0.0167 1.0000 14.250 1.5050 0.04050 0.03458 -0.0512 0.0164 1.0000 14.500 1.5124 0.04219 0.03633 -0.0503 0.0159 1.0000 14.750 1.5187 0.04401 0.03821 -0.0493 0.0154 1.0000 15.000 1.5245 0.04592 0.04018 -0.0484 0.0150 1.0000 15.250 1.5286 0.04804 0.04235 -0.0476 0.0146 1.0000 15.500 1.5306 0.05042 0.04480 -0.0467 0.0143 1.0000 15.750 1.5270 0.05347 0.04793 -0.0459 0.0139 1.0000 16.000 1.5254 0.05636 0.05090 -0.0452 0.0136 1.0000 16.250 1.5302 0.05860 0.05323 -0.0447 0.0134 1.0000 16.500 1.5351 0.06086 0.05556 -0.0444 0.0130 1.0000 16.750 1.5365 0.06356 0.05835 -0.0441 0.0128 1.0000 17.000 1.5392 0.06617 0.06102 -0.0439 0.0125 1.0000 17.250 1.5402 0.06901 0.06394 -0.0438 0.0122 1.0000 17.500 1.5406 0.07198 0.06698 -0.0438 0.0120 1.0000 17.750 1.5401 0.07512 0.07019 -0.0439 0.0118 1.0000 18.000 1.5374 0.07862 0.07377 -0.0442 0.0116 1.0000 18.250 1.5319 0.08258 0.07780 -0.0446 0.0114 1.0000 18.500 1.5238 0.08696 0.08228 -0.0453 0.0112 1.0000