XFOIL Version 6.96 Calculated polar for: NREL's S820 Airfoil 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 ------ -------- --------- --------- -------- -------- -------- -10.500 -0.3433 0.06247 0.05918 -0.1082 0.8126 0.0079 -8.500 -0.4350 0.03577 0.03099 -0.0912 0.7813 0.0045 -8.250 -0.4306 0.03334 0.02835 -0.0890 0.7784 0.0044 -8.000 -0.4221 0.03086 0.02562 -0.0870 0.7758 0.0043 -7.750 -0.4099 0.02848 0.02297 -0.0852 0.7734 0.0042 -7.500 -0.3944 0.02614 0.02034 -0.0837 0.7712 0.0041 -7.250 -0.3754 0.02367 0.01758 -0.0825 0.7690 0.0039 -7.000 -0.3529 0.02148 0.01511 -0.0817 0.7667 0.0038 -6.750 -0.3282 0.01976 0.01317 -0.0812 0.7646 0.0037 -6.500 -0.3032 0.01834 0.01157 -0.0808 0.7626 0.0036 -6.250 -0.2796 0.01712 0.01019 -0.0801 0.7606 0.0036 -6.000 -0.2580 0.01624 0.00920 -0.0793 0.7586 0.0037 -5.750 -0.2378 0.01549 0.00836 -0.0782 0.7568 0.0037 -5.500 -0.2187 0.01477 0.00755 -0.0771 0.7547 0.0038 -5.250 -0.1987 0.01419 0.00693 -0.0761 0.7524 0.0038 -5.000 -0.1785 0.01364 0.00632 -0.0751 0.7500 0.0040 -4.750 -0.1571 0.01317 0.00579 -0.0743 0.7478 0.0041 -4.500 -0.1348 0.01274 0.00530 -0.0737 0.7459 0.0044 -4.250 -0.1114 0.01239 0.00487 -0.0732 0.7440 0.0047 -4.000 -0.0877 0.01203 0.00445 -0.0728 0.7423 0.0053 -3.750 -0.0626 0.01177 0.00416 -0.0726 0.7406 0.0063 -3.500 -0.0373 0.01152 0.00389 -0.0725 0.7386 0.0080 -3.250 -0.0121 0.01126 0.00364 -0.0723 0.7364 0.0155 -3.000 0.0053 0.01021 0.00319 -0.0714 0.7341 0.1740 -2.750 0.0123 0.00812 0.00267 -0.0692 0.7318 0.5949 -2.500 0.0393 0.00826 0.00289 -0.0690 0.7300 0.6412 -2.250 0.0681 0.00832 0.00285 -0.0694 0.7284 0.6499 -2.000 0.0972 0.00832 0.00277 -0.0699 0.7269 0.6521 -1.750 0.1259 0.00831 0.00274 -0.0703 0.7251 0.6540 -1.500 0.1546 0.00830 0.00270 -0.0707 0.7231 0.6559 -1.250 0.1834 0.00830 0.00267 -0.0711 0.7209 0.6579 -1.000 0.2122 0.00830 0.00263 -0.0716 0.7189 0.6599 -0.750 0.2410 0.00831 0.00260 -0.0720 0.7170 0.6621 -0.500 0.2700 0.00832 0.00256 -0.0725 0.7153 0.6645 -0.250 0.2991 0.00834 0.00254 -0.0730 0.7137 0.6666 0.000 0.3279 0.00836 0.00256 -0.0735 0.7120 0.6684 0.250 0.3562 0.00837 0.00259 -0.0738 0.7098 0.6703 0.500 0.3846 0.00838 0.00262 -0.0742 0.7076 0.6723 0.750 0.4132 0.00841 0.00265 -0.0747 0.7055 0.6745 1.000 0.4419 0.00843 0.00267 -0.0751 0.7035 0.6768 1.250 0.4706 0.00846 0.00269 -0.0756 0.7015 0.6792 1.500 0.4995 0.00849 0.00272 -0.0760 0.6997 0.6815 1.750 0.5281 0.00852 0.00278 -0.0765 0.6979 0.6836 2.000 0.5559 0.00855 0.00286 -0.0767 0.6951 0.6857 2.250 0.5837 0.00856 0.00292 -0.0770 0.6915 0.6880 2.500 0.6115 0.00855 0.00291 -0.0772 0.6865 0.6904 2.750 0.6382 0.00853 0.00291 -0.0772 0.6784 0.6929 3.000 0.6650 0.00851 0.00286 -0.0771 0.6692 0.6953 3.250 0.6913 0.00850 0.00291 -0.0770 0.6602 0.6974 3.500 0.7178 0.00852 0.00296 -0.0770 0.6521 0.6997 3.750 0.7441 0.00855 0.00303 -0.0769 0.6437 0.7023 4.000 0.7702 0.00860 0.00311 -0.0768 0.6342 0.7051 4.250 0.7955 0.00866 0.00318 -0.0766 0.6218 0.7080 4.500 0.8196 0.00876 0.00327 -0.0760 0.6051 0.7107 4.750 0.8425 0.00889 0.00339 -0.0753 0.5865 0.7130 5.000 0.8631 0.00908 0.00354 -0.0741 0.5594 0.7156 5.250 0.8745 0.00953 0.00379 -0.0712 0.5069 0.7186 5.500 0.8781 0.01024 0.00422 -0.0669 0.4496 0.7218 5.750 0.8793 0.01091 0.00467 -0.0621 0.4018 0.7250 6.000 0.8800 0.01161 0.00521 -0.0575 0.3586 0.7280 6.250 0.8828 0.01240 0.00583 -0.0534 0.3158 0.7315 6.500 0.8895 0.01313 0.00642 -0.0502 0.2824 0.7354 6.750 0.8983 0.01383 0.00702 -0.0475 0.2527 0.7391 7.000 0.9069 0.01458 0.00767 -0.0449 0.2237 0.7424 7.500 0.9284 0.01601 0.00897 -0.0405 0.1765 0.7499 7.750 0.9395 0.01678 0.00966 -0.0386 0.1554 0.7539 8.000 0.9522 0.01749 0.01034 -0.0369 0.1389 0.7576 8.250 0.9653 0.01820 0.01104 -0.0353 0.1245 0.7619 8.500 0.9783 0.01895 0.01176 -0.0338 0.1100 0.7667 8.750 0.9916 0.01970 0.01250 -0.0323 0.0976 0.7714 9.000 1.0048 0.02045 0.01325 -0.0309 0.0872 0.7763 9.250 1.0194 0.02117 0.01399 -0.0297 0.0785 0.7817 9.500 1.0329 0.02195 0.01478 -0.0284 0.0694 0.7869 9.750 1.0462 0.02276 0.01561 -0.0271 0.0613 0.7930 10.250 1.0738 0.02434 0.01728 -0.0247 0.0490 0.8068 10.500 1.0861 0.02526 0.01821 -0.0235 0.0414 0.8146 10.750 1.0998 0.02606 0.01909 -0.0224 0.0369 0.8233 11.000 1.1115 0.02701 0.02008 -0.0211 0.0319 0.8329 11.250 1.1229 0.02799 0.02110 -0.0198 0.0256 0.8451 11.500 1.1342 0.02895 0.02215 -0.0185 0.0222 0.8610 11.750 1.1427 0.03003 0.02331 -0.0168 0.0171 0.8847 12.000 1.1561 0.03119 0.02458 -0.0164 0.0122 0.9477 12.500 1.1785 0.03358 0.02704 -0.0148 0.0078 1.0000 12.750 1.1892 0.03488 0.02838 -0.0139 0.0065 1.0000 13.000 1.1998 0.03620 0.02975 -0.0131 0.0052 1.0000 13.250 1.2103 0.03756 0.03118 -0.0124 0.0046 1.0000 13.500 1.2195 0.03906 0.03274 -0.0116 0.0040 1.0000 13.750 1.2294 0.04053 0.03429 -0.0109 0.0034 1.0000 14.000 1.2385 0.04210 0.03596 -0.0103 0.0030 1.0000 14.250 1.2459 0.04386 0.03779 -0.0096 0.0025 1.0000 14.500 1.2536 0.04563 0.03966 -0.0091 0.0020 1.0000 14.750 1.2609 0.04750 0.04162 -0.0086 0.0019 1.0000 15.000 1.2670 0.04950 0.04371 -0.0081 0.0017 1.0000 15.250 1.2697 0.05193 0.04624 -0.0077 0.0013 1.0000 15.500 1.2752 0.05410 0.04851 -0.0074 0.0011 1.0000 15.750 1.2791 0.05651 0.05104 -0.0072 0.0011 1.0000 16.000 1.2797 0.05938 0.05403 -0.0071 0.0009 1.0000 16.250 1.2826 0.06203 0.05679 -0.0072 0.0009 1.0000 16.500 1.2821 0.06514 0.06002 -0.0073 0.0008 1.0000 16.750 1.2779 0.06888 0.06392 -0.0077 0.0006 1.0000 17.000 1.2787 0.07208 0.06724 -0.0082 0.0007 1.0000 17.250 1.2753 0.07594 0.07123 -0.0091 0.0007 1.0000 17.500 1.2709 0.08006 0.07550 -0.0101 0.0007 1.0000 17.750 1.2593 0.08545 0.08105 -0.0117 0.0006 1.0000 18.000 1.2493 0.09082 0.08659 -0.0136 0.0006 1.0000 18.250 1.2407 0.09618 0.09211 -0.0158 0.0005 1.0000 18.500 1.2337 0.10134 0.09740 -0.0181 0.0006 1.0000 18.750 1.2185 0.10826 0.10449 -0.0213 0.0006 1.0000 19.000 1.2064 0.11478 0.11117 -0.0246 0.0005 1.0000