XFOIL Version 6.96 Calculated polar for: DELFT DU84-132V3 AIRFOIL (MEASURED) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.4468 0.08733 0.08354 -0.0534 1.0000 0.0281 -10.500 -0.4694 0.08019 0.07645 -0.0557 1.0000 0.0276 -10.250 -0.5613 0.05832 0.05432 -0.0724 0.9968 0.0265 -10.000 -0.5883 0.05038 0.04599 -0.0804 0.9855 0.0261 -9.750 -0.5979 0.04430 0.03945 -0.0846 0.9749 0.0258 -9.500 -0.5920 0.03934 0.03397 -0.0875 0.9683 0.0256 -9.250 -0.5834 0.03593 0.03014 -0.0879 0.9607 0.0255 -9.000 -0.5638 0.03323 0.02709 -0.0891 0.9559 0.0255 -8.750 -0.5385 0.03088 0.02441 -0.0907 0.9531 0.0255 -8.500 -0.5206 0.02917 0.02246 -0.0902 0.9464 0.0256 -8.250 -0.4948 0.02748 0.02053 -0.0910 0.9416 0.0257 -8.000 -0.4643 0.02589 0.01873 -0.0925 0.9386 0.0258 -7.750 -0.4384 0.02460 0.01726 -0.0928 0.9335 0.0260 -7.500 -0.4125 0.02345 0.01597 -0.0930 0.9282 0.0262 -7.250 -0.3817 0.02232 0.01472 -0.0941 0.9249 0.0265 -7.000 -0.3485 0.02126 0.01354 -0.0956 0.9225 0.0268 -6.750 -0.3229 0.02041 0.01262 -0.0955 0.9167 0.0271 -6.500 -0.2943 0.01956 0.01171 -0.0960 0.9116 0.0275 -6.250 -0.2621 0.01873 0.01080 -0.0972 0.9080 0.0279 -6.000 -0.2281 0.01796 0.00996 -0.0988 0.9052 0.0285 -5.750 -0.2061 0.01744 0.00940 -0.0979 0.8973 0.0292 -5.500 -0.1756 0.01685 0.00882 -0.0988 0.8926 0.0303 -5.250 -0.1417 0.01632 0.00827 -0.1003 0.8892 0.0315 -5.000 -0.1176 0.01592 0.00783 -0.0997 0.8814 0.0325 -4.750 -0.0870 0.01544 0.00730 -0.1005 0.8761 0.0338 -4.500 -0.0545 0.01499 0.00681 -0.1016 0.8717 0.0355 -4.250 -0.0284 0.01467 0.00646 -0.1013 0.8641 0.0383 -4.000 0.0035 0.01427 0.00600 -0.1022 0.8588 0.0432 -3.750 0.0322 0.01391 0.00558 -0.1025 0.8520 0.0506 -3.500 0.0611 0.01352 0.00521 -0.1028 0.8446 0.0610 -3.250 0.0889 0.01298 0.00488 -0.1031 0.8368 0.1009 -3.000 0.1154 0.01248 0.00463 -0.1032 0.8272 0.1711 -2.750 0.1408 0.01202 0.00444 -0.1031 0.8172 0.2440 -2.500 0.1689 0.01157 0.00423 -0.1034 0.8082 0.3138 -2.250 0.1947 0.01119 0.00411 -0.1032 0.7982 0.3969 -2.000 0.2196 0.01078 0.00401 -0.1028 0.7874 0.4778 -1.750 0.2436 0.01049 0.00411 -0.1017 0.7761 0.5763 -1.500 0.2679 0.01062 0.00447 -0.1002 0.7661 0.6488 -1.250 0.2960 0.01076 0.00454 -0.0998 0.7564 0.6857 -1.000 0.3233 0.01093 0.00463 -0.0993 0.7462 0.7048 -0.750 0.3499 0.01108 0.00470 -0.0988 0.7345 0.7202 -0.500 0.3771 0.01121 0.00473 -0.0985 0.7225 0.7333 -0.250 0.4037 0.01140 0.00484 -0.0978 0.7123 0.7425 0.000 0.4295 0.01160 0.00498 -0.0971 0.7015 0.7539 0.250 0.4551 0.01181 0.00514 -0.0963 0.6907 0.7666 0.500 0.4783 0.01199 0.00530 -0.0949 0.6783 0.7754 0.750 0.5042 0.01213 0.00535 -0.0943 0.6663 0.7842 1.000 0.5289 0.01224 0.00538 -0.0934 0.6538 0.7896 1.250 0.5544 0.01232 0.00541 -0.0928 0.6397 0.7948 1.500 0.5807 0.01240 0.00542 -0.0925 0.6273 0.7988 1.750 0.6059 0.01246 0.00543 -0.0919 0.6168 0.8015 2.000 0.6315 0.01254 0.00547 -0.0914 0.6064 0.8044 2.250 0.6566 0.01263 0.00553 -0.0908 0.5927 0.8083 2.500 0.6820 0.01277 0.00557 -0.0904 0.5777 0.8126 3.000 0.7281 0.01300 0.00570 -0.0882 0.5488 0.8206 3.250 0.7519 0.01314 0.00580 -0.0874 0.5329 0.8251 3.500 0.7762 0.01332 0.00590 -0.0868 0.5160 0.8282 3.750 0.7986 0.01348 0.00599 -0.0858 0.4992 0.8303 4.000 0.8207 0.01365 0.00611 -0.0847 0.4790 0.8323 4.250 0.8418 0.01383 0.00622 -0.0835 0.4454 0.8344 4.500 0.8605 0.01413 0.00636 -0.0819 0.4144 0.8365 4.750 0.8787 0.01450 0.00655 -0.0803 0.3888 0.8384 5.000 0.8996 0.01482 0.00679 -0.0792 0.3731 0.8400 5.250 0.9220 0.01509 0.00705 -0.0783 0.3598 0.8416 5.500 0.9444 0.01538 0.00731 -0.0775 0.3473 0.8431 5.750 0.9658 0.01565 0.00757 -0.0765 0.3352 0.8445 6.000 0.9865 0.01592 0.00783 -0.0754 0.3226 0.8461 6.250 1.0062 0.01621 0.00812 -0.0741 0.3114 0.8480 6.500 1.0245 0.01653 0.00842 -0.0725 0.3005 0.8501 6.750 1.0421 0.01689 0.00875 -0.0709 0.2882 0.8520 7.000 1.0615 0.01719 0.00907 -0.0695 0.2754 0.8540 7.250 1.0798 0.01756 0.00946 -0.0681 0.2655 0.8563 7.500 1.0968 0.01801 0.00987 -0.0665 0.2563 0.8582 7.750 1.1156 0.01838 0.01028 -0.0651 0.2463 0.8599 8.000 1.1337 0.01877 0.01072 -0.0637 0.2357 0.8616 8.250 1.1519 0.01918 0.01118 -0.0623 0.2203 0.8635 8.500 1.1663 0.01976 0.01171 -0.0605 0.1985 0.8655 8.750 1.1790 0.02047 0.01232 -0.0585 0.1772 0.8678 9.250 1.1989 0.02232 0.01395 -0.0541 0.1402 0.8726 9.500 1.2125 0.02307 0.01475 -0.0525 0.1303 0.8751 9.750 1.2259 0.02382 0.01557 -0.0508 0.1215 0.8781 10.000 1.2390 0.02462 0.01641 -0.0493 0.1101 0.8815 10.250 1.2497 0.02560 0.01738 -0.0475 0.1021 0.8852 10.500 1.2603 0.02662 0.01843 -0.0459 0.0958 0.8890 10.750 1.2708 0.02767 0.01953 -0.0444 0.0912 0.8942 11.000 1.2797 0.02887 0.02080 -0.0428 0.0873 0.9013 11.250 1.2911 0.02996 0.02202 -0.0416 0.0844 0.9130 11.500 1.3021 0.03100 0.02322 -0.0406 0.0813 0.9875 12.000 1.3151 0.03391 0.02625 -0.0376 0.0749 1.0000 12.250 1.3231 0.03544 0.02787 -0.0365 0.0718 1.0000 12.500 1.3336 0.03681 0.02937 -0.0357 0.0682 1.0000 12.750 1.3409 0.03848 0.03111 -0.0348 0.0645 1.0000 13.000 1.3462 0.04037 0.03306 -0.0340 0.0613 1.0000 13.250 1.3555 0.04196 0.03479 -0.0334 0.0571 1.0000 13.500 1.3612 0.04392 0.03682 -0.0328 0.0533 1.0000 13.750 1.3662 0.04602 0.03899 -0.0323 0.0502 1.0000 14.000 1.3701 0.04830 0.04133 -0.0319 0.0474 1.0000 14.250 1.3716 0.05089 0.04396 -0.0317 0.0450 1.0000 14.500 1.3721 0.05369 0.04684 -0.0316 0.0433 1.0000 14.750 1.3716 0.05670 0.04995 -0.0316 0.0417 1.0000 15.000 1.3692 0.06006 0.05339 -0.0319 0.0404 1.0000 15.250 1.3644 0.06382 0.05722 -0.0324 0.0391 1.0000 15.500 1.3588 0.06782 0.06128 -0.0331 0.0379 1.0000 15.750 1.3575 0.07135 0.06497 -0.0338 0.0367 1.0000 16.000 1.3547 0.07518 0.06894 -0.0347 0.0355 1.0000 16.250 1.3505 0.07930 0.07317 -0.0359 0.0343 1.0000 16.500 1.3451 0.08369 0.07766 -0.0373 0.0333 1.0000 16.750 1.3382 0.08838 0.08241 -0.0389 0.0325 1.0000