XFOIL Version 6.94 Calculated polar for: DAE-21 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6676 0.01385 0.00655 -0.1354 0.6854 0.0836 0.500 0.7196 0.01243 0.00672 -0.1353 0.6790 0.6111 1.000 0.7765 0.01174 0.00664 -0.1350 0.6709 1.0000 1.500 0.8344 0.01171 0.00638 -0.1351 0.6643 1.0000 2.000 0.8906 0.01190 0.00642 -0.1351 0.6570 1.0000 2.500 0.9460 0.01199 0.00644 -0.1349 0.6478 1.0000 3.000 1.0040 0.01195 0.00622 -0.1350 0.6404 1.0000 3.500 1.0575 0.01215 0.00645 -0.1347 0.6300 1.0000 4.000 1.1143 0.01211 0.00630 -0.1346 0.6205 1.0000 4.500 1.1676 0.01230 0.00652 -0.1343 0.6091 1.0000 5.000 1.2233 0.01231 0.00644 -0.1341 0.5978 1.0000 5.500 1.2745 0.01253 0.00675 -0.1334 0.5839 1.0000 6.000 1.3271 0.01271 0.00691 -0.1328 0.5701 1.0000 6.500 1.3785 0.01292 0.00708 -0.1321 0.5539 1.0000 7.000 1.4252 0.01325 0.00748 -0.1307 0.5350 1.0000 7.500 1.4698 0.01369 0.00795 -0.1289 0.5139 1.0000 8.000 1.5103 0.01427 0.00850 -0.1266 0.4903 1.0000 8.500 1.5432 0.01503 0.00930 -0.1231 0.4641 1.0000 9.000 1.5645 0.01600 0.01026 -0.1177 0.4371 1.0000 9.500 1.5707 0.01739 0.01162 -0.1103 0.4101 1.0000 10.000 1.5753 0.01935 0.01351 -0.1039 0.3820 1.0000 10.500 1.5807 0.02171 0.01585 -0.0984 0.3516 1.0000 11.000 1.5818 0.02466 0.01871 -0.0931 0.3210 1.0000 11.500 1.5849 0.02783 0.02184 -0.0887 0.2906 1.0000 12.000 1.5846 0.03151 0.02544 -0.0845 0.2607 1.0000 12.500 1.5854 0.03544 0.02934 -0.0809 0.2321 1.0000 13.000 1.5841 0.03995 0.03378 -0.0779 0.2037 1.0000 13.500 1.5832 0.04479 0.03859 -0.0754 0.1772 1.0000 14.000 1.5808 0.05014 0.04390 -0.0735 0.1521 1.0000 14.500 1.5780 0.05591 0.04965 -0.0720 0.1303 1.0000 15.000 1.5752 0.06202 0.05577 -0.0711 0.1112 1.0000 15.500 1.5694 0.06884 0.06260 -0.0708 0.0961 1.0000 16.000 1.5667 0.07560 0.06944 -0.0709 0.0833 1.0000 16.500 1.5624 0.08288 0.07682 -0.0715 0.0727 1.0000 17.000 1.5571 0.09060 0.08465 -0.0726 0.0641 1.0000 17.500 1.5513 0.09863 0.09279 -0.0742 0.0572 1.0000 18.000 1.5456 0.10681 0.10109 -0.0762 0.0516 1.0000 18.500 1.5406 0.11493 0.10928 -0.0786 0.0470 1.0000 19.000 1.5397 0.12257 0.11712 -0.0811 0.0428 1.0000 19.500 1.5397 0.12992 0.12462 -0.0838 0.0393 1.0000 20.000 1.5426 0.13652 0.13122 -0.0863 0.0364 1.0000 20.500 1.5446 0.14362 0.13859 -0.0894 0.0341 1.0000 21.000 1.5553 0.14846 0.14342 -0.0913 0.0319 1.0000 21.500 1.5560 0.15570 0.15098 -0.0950 0.0304 1.0000 22.000 1.5607 0.16192 0.15736 -0.0984 0.0289 1.0000 22.500 1.5709 0.16660 0.16211 -0.1008 0.0274 1.0000 23.000 1.5638 0.17534 0.17121 -0.1063 0.0264 1.0000 23.500 1.5576 0.18383 0.17999 -0.1119 0.0255 1.0000 24.000 1.5556 0.19131 0.18765 -0.1171 0.0247 1.0000 24.500 1.5581 0.19733 0.19378 -0.1214 0.0237 1.0000 25.000 1.5260 0.21229 0.20918 -0.1325 0.0234 1.0000 25.500 1.4777 0.23213 0.22948 -0.1474 0.0234 1.0000 26.500 1.0327 0.38313 0.38148 -0.1940 0.0244 1.0000 27.000 1.0335 0.39695 0.39531 -0.1979 0.0222 1.0000 27.500 1.0389 0.40534 0.40374 -0.2004 0.0206 1.0000 28.000 1.0390 0.41994 0.41836 -0.2044 0.0185 1.0000 28.500 1.0442 0.42793 0.42640 -0.2066 0.0173 1.0000 29.000 1.0436 0.44375 0.44223 -0.2106 0.0158 1.0000 29.500 1.0465 0.45370 0.45222 -0.2134 0.0146 1.0000 30.000 1.0482 0.46593 0.46447 -0.2163 0.0141 1.0000 30.500 1.0494 0.47845 0.47702 -0.2195 0.0123 1.0000 31.000 1.0522 0.48707 0.48568 -0.2217 0.0117 1.0000 31.500 1.0517 0.50360 0.50222 -0.2253 0.0106 1.0000 32.000 1.0529 0.51393 0.51259 -0.2280 0.0096 1.0000 32.500 1.0536 0.52488 0.52357 -0.2304 0.0093 1.0000 33.000 1.0536 0.53959 0.53830 -0.2336 0.0080 1.0000 33.500 1.0538 0.54923 0.54798 -0.2360 0.0074 1.0000 34.000 1.0533 0.56247 0.56124 -0.2387 0.0071 1.0000 34.500 1.0531 0.57642 0.57521 -0.2414 0.0061 1.0000 35.000 1.0522 0.58683 0.58565 -0.2439 0.0056 1.0000 35.500 1.0510 0.59607 0.59494 -0.2461 0.0054 1.0000 36.000 1.0494 0.61036 0.60923 -0.2488 0.0053 1.0000 36.500 1.0483 0.62391 0.62281 -0.2513 0.0047 1.0000 37.000 1.0463 0.63500 0.63393 -0.2536 0.0042 1.0000 37.500 1.0434 0.64283 0.64181 -0.2558 0.0038 1.0000 38.000 1.0410 0.65682 0.65581 -0.2582 0.0037 1.0000 38.500 1.0389 0.66982 0.66883 -0.2604 0.0031 1.0000 39.000 1.0356 0.68012 0.67916 -0.2626 0.0028 1.0000 39.500 1.0317 0.68932 0.68840 -0.2647 0.0026 1.0000 40.500 1.0244 0.71252 0.71164 -0.2689 0.0023 1.0000 41.000 1.0204 0.72334 0.72249 -0.2708 0.0020 1.0000 41.500 1.0158 0.73296 0.73214 -0.2728 0.0019 1.0000 42.000 1.0107 0.74208 0.74130 -0.2747 0.0017 1.0000 42.500 1.0053 0.75048 0.74972 -0.2767 0.0016 1.0000 43.000 0.9990 0.75797 0.75725 -0.2786 0.0015 1.0000 44.000 0.9876 0.77681 0.77614 -0.2820 0.0014 1.0000 44.500 0.9820 0.78619 0.78554 -0.2837 0.0013 1.0000 45.000 0.9755 0.79379 0.79316 -0.2853 0.0011 1.0000 45.500 0.9688 0.80151 0.80092 -0.2869 0.0010 1.0000 46.000 0.9615 0.80781 0.80725 -0.2885 0.0008 1.0000 46.500 0.9536 0.81315 0.81261 -0.2901 0.0007 1.0000 47.500 0.9380 0.82600 0.82550 -0.2930 0.0007 1.0000 48.000 0.9307 0.83288 0.83240 -0.2942 0.0007 1.0000 48.500 0.9229 0.83903 0.83858 -0.2955 0.0006 1.0000 49.000 0.9144 0.84356 0.84313 -0.2968 0.0005 1.0000 49.500 0.9057 0.84786 0.84747 -0.2980 0.0005 1.0000 50.000 0.8966 0.85117 0.85080 -0.2992 0.0004 1.0000 50.500 0.8873 0.85412 0.85377 -0.3003 0.0003 1.0000 51.000 0.8778 0.85659 0.85627 -0.3015 0.0003 1.0000 51.500 0.8680 0.85838 0.85809 -0.3026 0.0003 1.0000 52.000 0.8575 0.85906 0.85879 -0.3037 0.0002 1.0000 53.500 0.8279 0.86372 0.86351 -0.3063 0.0002 1.0000 54.000 0.8176 0.86390 0.86372 -0.3070 0.0002 1.0000 54.500 0.8068 0.86310 0.86293 -0.3078 0.0001 1.0000 55.000 0.7960 0.86195 0.86181 -0.3085 0.0001 1.0000 55.500 0.7847 0.85984 0.85972 -0.3092 0.0001 1.0000 56.500 0.7628 0.85687 0.85677 -0.3103 0.0001 1.0000 57.000 0.7514 0.85376 0.85369 -0.3109 0.0001 1.0000 57.500 0.7400 0.85085 0.85080 -0.3113 0.0001 1.0000 58.000 0.7283 0.84672 0.84669 -0.3117 0.0000 1.0000 58.500 0.7165 0.84221 0.84220 -0.3121 0.0000 1.0000 59.000 0.7046 0.83713 0.83714 -0.3124 0.0000 1.0000 59.500 0.6925 0.83161 0.83162 -0.3128 0.0000 1.0000