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 = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6738 0.01090 0.00404 -0.1344 0.6667 0.0648 0.500 0.7300 0.00996 0.00402 -0.1350 0.6601 0.4104 1.000 0.7846 0.00870 0.00410 -0.1345 0.6533 1.0000 1.500 0.8420 0.00875 0.00399 -0.1347 0.6458 1.0000 2.000 0.8993 0.00890 0.00396 -0.1348 0.6381 1.0000 2.500 0.9554 0.00899 0.00402 -0.1349 0.6294 1.0000 3.000 1.0121 0.00907 0.00398 -0.1349 0.6205 1.0000 3.500 1.0675 0.00923 0.00412 -0.1349 0.6104 1.0000 4.000 1.1230 0.00935 0.00418 -0.1348 0.5996 1.0000 4.500 1.1774 0.00954 0.00438 -0.1347 0.5876 1.0000 5.500 1.2842 0.00998 0.00479 -0.1340 0.5603 1.0000 6.000 1.3359 0.01028 0.00509 -0.1334 0.5442 1.0000 6.500 1.3857 0.01064 0.00545 -0.1326 0.5260 1.0000 7.000 1.4331 0.01109 0.00587 -0.1314 0.5051 1.0000 7.500 1.4771 0.01165 0.00642 -0.1296 0.4813 1.0000 8.000 1.5156 0.01237 0.00709 -0.1270 0.4543 1.0000 8.500 1.5452 0.01331 0.00796 -0.1230 0.4266 1.0000 9.000 1.5595 0.01439 0.00901 -0.1164 0.3992 1.0000 9.500 1.5657 0.01602 0.01061 -0.1095 0.3705 1.0000 10.000 1.5691 0.01830 0.01278 -0.1033 0.3407 1.0000 10.500 1.5768 0.02075 0.01518 -0.0982 0.3098 1.0000 11.000 1.5800 0.02375 0.01808 -0.0933 0.2797 1.0000 11.500 1.5857 0.02685 0.02112 -0.0892 0.2503 1.0000 12.000 1.5876 0.03046 0.02464 -0.0852 0.2215 1.0000 12.500 1.5913 0.03422 0.02834 -0.0818 0.1941 1.0000 13.000 1.5929 0.03847 0.03252 -0.0788 0.1673 1.0000 13.500 1.5957 0.04295 0.03694 -0.0764 0.1428 1.0000 14.000 1.5966 0.04788 0.04182 -0.0744 0.1215 1.0000 14.500 1.5993 0.05294 0.04688 -0.0729 0.1034 1.0000 15.000 1.6000 0.05849 0.05245 -0.0718 0.0880 1.0000 15.500 1.5992 0.06452 0.05851 -0.0712 0.0756 1.0000 16.000 1.5998 0.07067 0.06475 -0.0710 0.0655 1.0000 16.500 1.5980 0.07744 0.07161 -0.0713 0.0573 1.0000 17.000 1.5942 0.08475 0.07905 -0.0721 0.0506 1.0000 17.500 1.5889 0.09259 0.08702 -0.0735 0.0451 1.0000 18.000 1.5809 0.10109 0.09564 -0.0755 0.0407 1.0000 18.500 1.5741 0.10963 0.10433 -0.0779 0.0370 1.0000 19.000 1.5692 0.11799 0.11288 -0.0806 0.0339 1.0000 19.500 1.5594 0.12721 0.12221 -0.0841 0.0316 1.0000 20.000 1.5575 0.13517 0.13038 -0.0874 0.0295 1.0000 20.500 1.5516 0.14361 0.13889 -0.0912 0.0277 1.0000 21.000 1.5522 0.15103 0.14654 -0.0947 0.0262 1.0000 21.500 1.5517 0.15854 0.15418 -0.0987 0.0249 1.0000 22.000 1.5533 0.16529 0.16101 -0.1024 0.0236 1.0000 22.500 1.5533 0.17272 0.16868 -0.1068 0.0224 1.0000 23.000 1.5541 0.17980 0.17589 -0.1112 0.0214 1.0000 23.500 1.5601 0.18529 0.18141 -0.1148 0.0203 1.0000 24.000 1.5557 0.19359 0.18998 -0.1204 0.0195 1.0000 24.500 1.5523 0.20153 0.19813 -0.1261 0.0187 1.0000 25.000 1.5522 0.20864 0.20535 -0.1314 0.0179 1.0000 25.500 1.5541 0.21484 0.21163 -0.1362 0.0171 1.0000 26.000 1.5421 0.22480 0.22189 -0.1439 0.0166 1.0000 26.500 1.5290 0.23507 0.23242 -0.1519 0.0161 1.0000 27.000 1.5134 0.24617 0.24377 -0.1607 0.0156 1.0000 27.500 1.4958 0.25804 0.25585 -0.1700 0.0151 1.0000 28.000 1.4980 0.26407 0.26191 -0.1754 0.0144 1.0000 29.000 1.3596 0.35034 0.34827 -0.2198 0.0131 1.0000 29.500 1.3695 0.35444 0.35240 -0.2237 0.0121 1.0000 30.500 1.3857 0.36739 0.36536 -0.2332 0.0103 1.0000 31.000 1.3945 0.37105 0.36905 -0.2371 0.0096 1.0000 31.500 1.4046 0.37304 0.37110 -0.2397 0.0093 1.0000 32.000 1.4103 0.38304 0.38106 -0.2464 0.0081 1.0000 32.500 1.4178 0.38677 0.38481 -0.2505 0.0076 1.0000 33.000 1.4257 0.38881 0.38691 -0.2537 0.0073 1.0000 33.500 1.4329 0.39776 0.39582 -0.2596 0.0064 1.0000 34.000 1.4394 0.40123 0.39932 -0.2638 0.0057 1.0000 34.500 1.4452 0.40369 0.40182 -0.2675 0.0055 1.0000 35.000 1.4525 0.41085 0.40897 -0.2726 0.0051 1.0000 35.500 1.4589 0.41520 0.41333 -0.2769 0.0043 1.0000 36.000 1.4635 0.41748 0.41564 -0.2810 0.0039 1.0000 36.500 1.4682 0.41924 0.41745 -0.2845 0.0038 1.0000 37.000 1.4759 0.42631 0.42449 -0.2900 0.0034 1.0000 37.500 1.4809 0.42965 0.42785 -0.2944 0.0029 1.0000 38.000 1.4848 0.43222 0.43045 -0.2987 0.0028 1.0000 39.000 1.0367 0.67712 0.67635 -0.2639 0.0014 1.0000 39.500 1.0341 0.69262 0.69184 -0.2661 0.0014 1.0000 40.000 1.0309 0.70470 0.70395 -0.2681 0.0012 1.0000 40.500 1.0269 0.71511 0.71439 -0.2702 0.0010 1.0000 41.000 1.0223 0.72437 0.72367 -0.2722 0.0008 1.0000 41.500 1.0173 0.73309 0.73242 -0.2742 0.0008 1.0000 42.000 1.0116 0.74083 0.74019 -0.2762 0.0007 1.0000 43.000 1.0009 0.76090 0.76030 -0.2798 0.0007 1.0000 43.500 0.9957 0.77102 0.77044 -0.2815 0.0007 1.0000 44.000 0.9902 0.78031 0.77974 -0.2832 0.0005 1.0000 44.500 0.9840 0.78863 0.78809 -0.2848 0.0005 1.0000 45.000 0.9771 0.79562 0.79510 -0.2865 0.0004 1.0000 45.500 0.9702 0.80280 0.80231 -0.2882 0.0003 1.0000 46.000 0.9624 0.80820 0.80773 -0.2898 0.0003 1.0000 47.000 0.9483 0.82404 0.82360 -0.2925 0.0002 1.0000 47.500 0.9406 0.83005 0.82964 -0.2940 0.0001 1.0000 48.000 0.9322 0.83475 0.83436 -0.2953 0.0001 1.0000 49.000 0.9152 0.84458 0.84422 -0.2979 0.0001 1.0000 49.500 0.9069 0.84983 0.84950 -0.2991 0.0001 1.0000 50.000 0.8978 0.85345 0.85314 -0.3002 0.0001 1.0000 50.500 0.8886 0.85678 0.85649 -0.3013 0.0000 1.0000 51.000 0.8792 0.85946 0.85918 -0.3024 0.0000 1.0000 51.500 0.8695 0.86146 0.86121 -0.3035 0.0000 1.0000 52.000 0.8593 0.86235 0.86212 -0.3045 0.0000 1.0000 54.000 0.8184 0.86595 0.86579 -0.3080 0.0000 1.0000 54.500 0.8078 0.86569 0.86554 -0.3087 0.0000 1.0000 55.000 0.7971 0.86512 0.86500 -0.3093 0.0000 1.0000 55.500 0.7862 0.86375 0.86364 -0.3100 0.0000 1.0000 56.000 0.7751 0.86197 0.86188 -0.3105 0.0000 1.0000 56.500 0.7640 0.85992 0.85984 -0.3111 0.0000 1.0000 57.000 0.7524 0.85659 0.85653 -0.3117 0.0000 1.0000 57.500 0.7409 0.85332 0.85327 -0.3121 0.0000 1.0000 58.000 0.7291 0.84899 0.84896 -0.3125 0.0000 1.0000 58.500 0.7173 0.84444 0.84442 -0.3130 0.0000 1.0000 59.000 0.7053 0.83921 0.83921 -0.3133 0.0001 1.0000 59.500 0.6932 0.83361 0.83362 -0.3136 0.0001 1.0000 60.000 0.6808 0.82727 0.82730 -0.3139 0.0001 1.0000