XFOIL Version 6.96 Calculated polar for: SD2083 (9.0%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.4040 0.08812 0.08588 -0.0354 1.0000 0.0097 -9.000 -0.4058 0.08398 0.08178 -0.0372 1.0000 0.0098 -8.750 -0.4092 0.07990 0.07774 -0.0389 1.0000 0.0096 -8.500 -0.4079 0.07496 0.07283 -0.0431 0.9883 0.0097 -8.000 -0.3909 0.05934 0.05713 -0.0653 0.9500 0.0097 -7.750 -0.3909 0.05234 0.04998 -0.0709 0.9334 0.0098 -7.500 -0.3919 0.04558 0.04300 -0.0735 0.9204 0.0098 -7.250 -0.3917 0.03849 0.03557 -0.0744 0.9100 0.0098 -7.000 -0.3869 0.03226 0.02891 -0.0740 0.9017 0.0100 -6.750 -0.3754 0.02769 0.02391 -0.0732 0.8943 0.0103 -6.500 -0.3606 0.02409 0.01983 -0.0721 0.8883 0.0105 -6.250 -0.3424 0.02115 0.01645 -0.0711 0.8825 0.0105 -6.000 -0.3214 0.01900 0.01393 -0.0702 0.8770 0.0106 -5.750 -0.2986 0.01739 0.01200 -0.0694 0.8725 0.0108 -5.500 -0.2743 0.01609 0.01043 -0.0689 0.8672 0.0111 -5.250 -0.2495 0.01507 0.00921 -0.0684 0.8624 0.0114 -5.000 -0.2241 0.01425 0.00822 -0.0679 0.8579 0.0118 -4.750 -0.1982 0.01356 0.00740 -0.0675 0.8527 0.0120 -4.500 -0.1721 0.01300 0.00672 -0.0672 0.8479 0.0123 -4.250 -0.1460 0.01248 0.00610 -0.0668 0.8435 0.0124 -4.000 -0.1206 0.01168 0.00521 -0.0664 0.8382 0.0127 -3.750 -0.0956 0.01092 0.00434 -0.0659 0.8334 0.0137 -3.500 -0.0693 0.01049 0.00384 -0.0656 0.8287 0.0143 -3.250 -0.0427 0.01011 0.00340 -0.0653 0.8233 0.0145 -3.000 -0.0160 0.00981 0.00302 -0.0650 0.8185 0.0148 -2.750 0.0111 0.00954 0.00270 -0.0648 0.8132 0.0153 -2.500 0.0383 0.00932 0.00240 -0.0646 0.8077 0.0161 -2.250 0.0655 0.00914 0.00216 -0.0644 0.8027 0.0172 -2.000 0.0930 0.00898 0.00195 -0.0643 0.7964 0.0190 -1.500 0.1471 0.00856 0.00165 -0.0639 0.7841 0.0620 -1.250 0.1732 0.00819 0.00153 -0.0637 0.7772 0.1372 -1.000 0.1994 0.00785 0.00144 -0.0636 0.7697 0.2221 -0.750 0.2254 0.00755 0.00136 -0.0634 0.7621 0.3108 -0.500 0.2503 0.00708 0.00133 -0.0630 0.7534 0.4510 -0.250 0.2716 0.00642 0.00135 -0.0618 0.7449 0.6621 0.000 0.2918 0.00594 0.00138 -0.0599 0.7354 0.8210 0.250 0.3289 0.00576 0.00143 -0.0613 0.7249 0.9384 0.500 0.3702 0.00579 0.00140 -0.0642 0.7132 0.9697 0.750 0.4097 0.00584 0.00137 -0.0667 0.6994 0.9846 1.000 0.4474 0.00590 0.00135 -0.0689 0.6847 0.9947 1.250 0.4814 0.00597 0.00134 -0.0703 0.6704 1.0000 1.500 0.5062 0.00605 0.00136 -0.0697 0.6562 1.0000 1.750 0.5310 0.00616 0.00139 -0.0690 0.6401 1.0000 2.250 0.5803 0.00641 0.00149 -0.0677 0.6040 1.0000 2.500 0.6046 0.00657 0.00156 -0.0670 0.5821 1.0000 2.750 0.6286 0.00676 0.00166 -0.0663 0.5570 1.0000 3.000 0.6522 0.00699 0.00177 -0.0655 0.5278 1.0000 3.250 0.6754 0.00726 0.00191 -0.0646 0.4947 1.0000 3.500 0.6980 0.00759 0.00207 -0.0637 0.4567 1.0000 3.750 0.7206 0.00793 0.00228 -0.0628 0.4195 1.0000 4.000 0.7433 0.00830 0.00249 -0.0619 0.3839 1.0000 4.250 0.7659 0.00867 0.00271 -0.0611 0.3484 1.0000 4.500 0.7887 0.00904 0.00295 -0.0603 0.3168 1.0000 4.750 0.8117 0.00940 0.00319 -0.0595 0.2877 1.0000 5.000 0.8346 0.00978 0.00348 -0.0588 0.2591 1.0000 5.250 0.8560 0.01028 0.00379 -0.0578 0.2197 1.0000 5.500 0.8771 0.01083 0.00413 -0.0569 0.1792 1.0000 5.750 0.8991 0.01129 0.00445 -0.0560 0.1504 1.0000 6.000 0.9201 0.01185 0.00483 -0.0550 0.1154 1.0000 6.250 0.9415 0.01236 0.00522 -0.0541 0.0904 1.0000 6.500 0.9627 0.01288 0.00566 -0.0532 0.0689 1.0000 6.750 0.9833 0.01346 0.00613 -0.0521 0.0480 1.0000 7.000 1.0010 0.01431 0.00677 -0.0507 0.0190 1.0000 7.250 1.0205 0.01497 0.00738 -0.0495 0.0089 1.0000 7.500 1.0420 0.01544 0.00789 -0.0485 0.0078 1.0000 7.750 1.0626 0.01597 0.00848 -0.0474 0.0068 1.0000 8.000 1.0828 0.01653 0.00914 -0.0463 0.0062 1.0000 8.250 1.1019 0.01717 0.00987 -0.0450 0.0058 1.0000 8.500 1.1184 0.01803 0.01086 -0.0432 0.0053 1.0000 8.750 1.1361 0.01872 0.01163 -0.0418 0.0052 1.0000 9.000 1.1529 0.01943 0.01242 -0.0402 0.0051 1.0000 9.250 1.1686 0.02016 0.01324 -0.0385 0.0049 1.0000 9.500 1.1826 0.02086 0.01402 -0.0365 0.0046 1.0000 9.750 1.1938 0.02171 0.01496 -0.0341 0.0044 1.0000 10.000 1.2044 0.02262 0.01599 -0.0317 0.0043 1.0000 10.250 1.2142 0.02361 0.01708 -0.0294 0.0041 1.0000 10.500 1.2236 0.02466 0.01824 -0.0272 0.0040 1.0000 10.750 1.2315 0.02586 0.01954 -0.0250 0.0039 1.0000 11.000 1.2393 0.02710 0.02089 -0.0229 0.0038 1.0000 11.250 1.2460 0.02847 0.02237 -0.0208 0.0037 1.0000 11.500 1.2521 0.02992 0.02394 -0.0189 0.0036 1.0000 11.750 1.2559 0.03165 0.02579 -0.0169 0.0036 1.0000 12.000 1.2606 0.03331 0.02757 -0.0153 0.0035 1.0000 12.250 1.2635 0.03523 0.02963 -0.0137 0.0035 1.0000 12.500 1.2641 0.03742 0.03194 -0.0122 0.0033 1.0000 12.750 1.2641 0.03975 0.03444 -0.0109 0.0033 1.0000 13.000 1.2614 0.04248 0.03732 -0.0099 0.0032 1.0000 13.250 1.2600 0.04520 0.04019 -0.0091 0.0032 1.0000 13.500 1.2507 0.04897 0.04415 -0.0086 0.0031 1.0000 13.750 1.2391 0.05326 0.04863 -0.0085 0.0030 1.0000 14.000 1.2272 0.05784 0.05340 -0.0091 0.0030 1.0000 14.250 1.2218 0.06175 0.05747 -0.0100 0.0030 1.0000 14.500 1.2060 0.06755 0.06348 -0.0118 0.0030 1.0000 14.750 1.1977 0.07253 0.06861 -0.0138 0.0030 1.0000 15.000 1.1748 0.08040 0.07670 -0.0174 0.0029 1.0000 15.250 1.1680 0.08584 0.08227 -0.0203 0.0030 1.0000 15.500 1.1588 0.09202 0.08859 -0.0236 0.0030 1.0000 15.750 1.1355 0.10141 0.09818 -0.0289 0.0030 1.0000 16.000 1.1253 0.10844 0.10533 -0.0330 0.0030 1.0000