XFOIL Version 6.96 Calculated polar for: DU 06-W-200 VAWT airfoil 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.000 -0.7344 0.12330 0.11532 0.0000 1.0000 0.1418 -14.750 -0.7105 0.12436 0.11634 0.0014 1.0000 0.1451 -14.500 -0.8662 0.09024 0.08208 -0.0168 1.0000 0.1559 -14.250 -0.7764 0.10253 0.09448 -0.0092 1.0000 0.1590 -14.000 -0.8546 0.08526 0.07704 -0.0177 1.0000 0.1661 -13.750 -0.9394 0.07029 0.06164 -0.0241 1.0000 0.1700 -13.500 -0.9010 0.07216 0.06368 -0.0223 1.0000 0.1762 -13.250 -0.9216 0.06662 0.05796 -0.0238 1.0000 0.1817 -13.000 -0.9469 0.06090 0.05197 -0.0251 1.0000 0.1867 -12.750 -0.9222 0.06083 0.05202 -0.0243 1.0000 0.1934 -12.500 -0.9366 0.05662 0.04759 -0.0248 1.0000 0.1997 -12.250 -0.9234 0.05524 0.04624 -0.0244 1.0000 0.2064 -12.000 -0.9211 0.05287 0.04378 -0.0242 1.0000 0.2136 -11.750 -0.9166 0.05070 0.04154 -0.0239 1.0000 0.2210 -11.500 -0.9057 0.04922 0.04003 -0.0235 1.0000 0.2289 -11.250 -0.9003 0.04719 0.03792 -0.0231 1.0000 0.2369 -11.000 -0.8876 0.04592 0.03664 -0.0226 1.0000 0.2457 -10.750 -0.8772 0.04440 0.03510 -0.0221 1.0000 0.2546 -10.500 -0.8669 0.04292 0.03358 -0.0215 1.0000 0.2640 -10.250 -0.8503 0.04198 0.03268 -0.0209 1.0000 0.2736 -10.000 -0.8467 0.04010 0.03069 -0.0202 1.0000 0.2842 -9.750 -0.8235 0.03969 0.03039 -0.0196 1.0000 0.2943 -9.500 -0.8103 0.03860 0.02933 -0.0188 1.0000 0.3052 -9.250 -0.8033 0.03721 0.02788 -0.0179 1.0000 0.3170 -9.000 -0.7807 0.03688 0.02767 -0.0172 1.0000 0.3282 -8.750 -0.7658 0.03614 0.02698 -0.0162 1.0000 0.3403 -8.500 -0.7554 0.03515 0.02602 -0.0152 1.0000 0.3531 -8.250 -0.7405 0.03455 0.02548 -0.0142 1.0000 0.3660 -8.000 -0.7220 0.03435 0.02539 -0.0130 1.0000 0.3783 -7.750 -0.7132 0.03394 0.02508 -0.0111 1.0000 0.3905 -7.500 -0.6993 0.03347 0.02463 -0.0105 0.9877 0.4045 -7.250 -0.6562 0.03335 0.02450 -0.0136 0.9649 0.4215 -7.000 -0.6164 0.03326 0.02436 -0.0159 0.9422 0.4377 -6.750 -0.5789 0.03320 0.02424 -0.0176 0.9207 0.4537 -6.500 -0.5347 0.03405 0.02506 -0.0185 0.9018 0.4649 -6.250 -0.4998 0.03450 0.02543 -0.0186 0.8827 0.4767 -6.000 -0.4742 0.03450 0.02531 -0.0181 0.8640 0.4899 -5.750 -0.4450 0.03507 0.02578 -0.0170 0.8465 0.5001 -5.500 -0.4177 0.03560 0.02621 -0.0158 0.8301 0.5094 -5.250 -0.3987 0.03545 0.02595 -0.0146 0.8144 0.5224 -5.000 -0.3674 0.03645 0.02685 -0.0131 0.8000 0.5285 -4.750 -0.3477 0.03641 0.02669 -0.0120 0.7867 0.5403 -4.500 -0.3210 0.03698 0.02713 -0.0105 0.7747 0.5483 -4.250 -0.2986 0.03711 0.02719 -0.0096 0.7617 0.5585 -4.000 -0.2811 0.03687 0.02684 -0.0087 0.7502 0.5714 -3.750 -0.2519 0.03747 0.02733 -0.0074 0.7401 0.5778 -3.500 -0.2329 0.03732 0.02711 -0.0068 0.7287 0.5896 -3.250 -0.2163 0.03700 0.02668 -0.0059 0.7198 0.6029 -3.000 -0.1869 0.03751 0.02714 -0.0051 0.7094 0.6087 -2.750 -0.1693 0.03725 0.02679 -0.0043 0.7008 0.6209 -2.500 -0.1434 0.03748 0.02697 -0.0036 0.6914 0.6285 -2.250 -0.1236 0.03734 0.02675 -0.0028 0.6834 0.6390 -2.000 -0.1081 0.03702 0.02638 -0.0022 0.6747 0.6520 -1.750 -0.0785 0.03729 0.02658 -0.0014 0.6674 0.6570 -1.500 -0.0626 0.03703 0.02628 -0.0009 0.6585 0.6693 -1.250 -0.0338 0.03716 0.02635 0.0000 0.6522 0.6745 -1.000 -0.0182 0.03698 0.02615 0.0004 0.6434 0.6863 -0.750 0.0097 0.03706 0.02619 0.0012 0.6365 0.6915 -0.500 0.0258 0.03686 0.02595 0.0018 0.6291 0.7027 -0.250 0.0523 0.03696 0.02605 0.0025 0.6215 0.7078 0.000 0.0745 0.03677 0.02578 0.0033 0.6157 0.7162 0.250 0.0942 0.03685 0.02591 0.0039 0.6071 0.7236 0.500 0.1184 0.03672 0.02572 0.0047 0.6010 0.7306 0.750 0.1359 0.03671 0.02571 0.0054 0.5932 0.7390 1.000 0.1601 0.03671 0.02571 0.0061 0.5862 0.7448 1.250 0.1792 0.03644 0.02536 0.0068 0.5808 0.7539 1.500 0.2006 0.03669 0.02570 0.0076 0.5719 0.7588 1.750 0.2243 0.03650 0.02546 0.0083 0.5661 0.7655 2.000 0.2411 0.03664 0.02564 0.0091 0.5579 0.7725 2.250 0.2647 0.03660 0.02562 0.0098 0.5509 0.7778 2.500 0.2862 0.03650 0.02547 0.0105 0.5449 0.7847 2.750 0.3035 0.03674 0.02579 0.0113 0.5360 0.7904 3.000 0.3299 0.03650 0.02551 0.0120 0.5306 0.7956 3.250 0.3438 0.03692 0.02601 0.0128 0.5214 0.8022 3.500 0.3680 0.03677 0.02585 0.0134 0.5149 0.8070 3.750 0.3871 0.03702 0.02617 0.0143 0.5069 0.8120 4.000 0.4069 0.03713 0.02630 0.0149 0.4991 0.8177 4.250 0.4323 0.03694 0.02608 0.0153 0.4931 0.8225 4.500 0.4458 0.03754 0.02681 0.0164 0.4833 0.8271 4.750 0.4744 0.03717 0.02639 0.0167 0.4778 0.8319 5.000 0.4836 0.03806 0.02741 0.0175 0.4673 0.8373 5.250 0.5114 0.03775 0.02710 0.0180 0.4614 0.8410 5.500 0.5214 0.03861 0.02810 0.0191 0.4512 0.8456 5.750 0.5486 0.03839 0.02787 0.0193 0.4447 0.8499 6.000 0.5590 0.03935 0.02896 0.0199 0.4349 0.8545 6.250 0.5848 0.03919 0.02882 0.0204 0.4280 0.8579 6.500 0.5943 0.04018 0.02994 0.0212 0.4183 0.8622 6.750 0.6198 0.04015 0.02993 0.0214 0.4112 0.8660 7.000 0.6286 0.04139 0.03129 0.0217 0.4014 0.8700 7.250 0.6539 0.04124 0.03118 0.0221 0.3943 0.8732 7.500 0.6572 0.04280 0.03287 0.0228 0.3843 0.8772 7.750 0.6837 0.04270 0.03281 0.0229 0.3776 0.8809 8.000 0.6804 0.04489 0.03513 0.0233 0.3673 0.8851 8.250 0.7094 0.04457 0.03484 0.0234 0.3610 0.8880 8.500 0.6948 0.04794 0.03837 0.0234 0.3501 0.8923 8.750 0.7261 0.04733 0.03779 0.0237 0.3445 0.8961 9.000 0.7087 0.05195 0.04255 0.0220 0.3327 0.9009 9.250 0.7435 0.05080 0.04144 0.0227 0.3280 0.9046 9.750 0.7533 0.05551 0.04633 0.0211 0.3115 0.9130 10.250 0.7565 0.06140 0.05242 0.0188 0.2950 0.9225 10.500 0.8051 0.05838 0.04941 0.0204 0.2928 0.9285 10.750 0.7512 0.06881 0.06002 0.0159 0.2785 0.9347 11.000 0.7982 0.06574 0.05699 0.0174 0.2765 0.9431 11.250 0.7414 0.07747 0.06887 0.0121 0.2621 0.9509 11.750 0.7240 0.08737 0.07893 0.0074 0.2460 1.0000 12.250 0.7083 0.09864 0.09031 0.0016 0.2309 1.0000 12.500 0.7228 0.10075 0.09248 0.0004 0.2267 1.0000 13.000 0.7197 0.11018 0.10202 -0.0046 0.2138 1.0000 13.500 0.6995 0.12283 0.11477 -0.0114 0.2008 1.0000 13.750 0.7242 0.12326 0.11525 -0.0118 0.1977 1.0000