XFOIL Version 6.96 Calculated polar for: EPPLER 336 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.4405 0.08555 0.08347 -0.0190 1.0000 0.0156 -9.000 -0.4488 0.08015 0.07811 -0.0235 1.0000 0.0156 -8.750 -0.4637 0.07480 0.07274 -0.0270 1.0000 0.0158 -8.500 -0.4777 0.07091 0.06882 -0.0272 1.0000 0.0157 -8.250 -0.4943 0.06741 0.06527 -0.0253 1.0000 0.0159 -8.000 -0.5061 0.06420 0.06200 -0.0228 1.0000 0.0160 -7.750 -0.5191 0.05847 0.05601 -0.0197 1.0000 0.0165 -7.500 -0.4982 0.05081 0.04794 -0.0246 0.9103 0.0168 -7.250 -0.4892 0.04852 0.04533 -0.0237 0.8289 0.0170 -7.000 -0.4844 0.04661 0.04317 -0.0212 0.7879 0.0172 -6.750 -0.4770 0.04467 0.04101 -0.0189 0.7585 0.0175 -6.500 -0.4683 0.04259 0.03870 -0.0166 0.7350 0.0179 -6.250 -0.4580 0.04027 0.03614 -0.0142 0.7146 0.0184 -6.000 -0.4501 0.03753 0.03262 -0.0086 0.6990 0.0205 -5.750 -0.4399 0.03353 0.02854 -0.0070 0.6830 0.0210 -5.500 -0.4236 0.03191 0.02680 -0.0056 0.6668 0.0214 -5.250 -0.4065 0.03042 0.02513 -0.0040 0.6521 0.0221 -4.750 -0.3723 0.02633 0.02034 0.0008 0.6270 0.0260 -4.500 -0.3510 0.02501 0.01892 0.0018 0.6148 0.0270 -4.250 -0.3289 0.02392 0.01759 0.0032 0.6033 0.0290 -4.000 -0.2935 0.01697 0.00964 0.0057 0.5946 0.0124 -3.750 -0.2643 0.01541 0.00785 0.0060 0.5839 0.0115 -3.500 -0.2377 0.01443 0.00668 0.0066 0.5736 0.0111 -3.250 -0.2129 0.01371 0.00588 0.0075 0.5632 0.0111 -3.000 -0.1892 0.01315 0.00526 0.0085 0.5538 0.0113 -2.750 -0.1659 0.01268 0.00473 0.0095 0.5443 0.0119 -2.500 -0.1422 0.01230 0.00428 0.0105 0.5354 0.0127 -2.250 -0.1191 0.01190 0.00381 0.0116 0.5266 0.0141 -2.000 -0.0951 0.01157 0.00345 0.0126 0.5179 0.0177 -1.750 -0.0728 0.01115 0.00308 0.0139 0.5097 0.0394 -1.500 -0.0544 0.01042 0.00287 0.0155 0.5014 0.1669 -1.250 -0.0667 0.00832 0.00246 0.0229 0.4957 0.6100 -1.000 -0.0540 0.00815 0.00326 0.0276 0.4882 0.8811 -0.750 -0.0126 0.00950 0.00451 0.0267 0.4782 0.9129 -0.500 0.0915 0.01092 0.00569 0.0123 0.4629 0.9206 -0.250 0.1318 0.01147 0.00613 0.0104 0.4521 0.9314 0.000 0.2068 0.01199 0.00647 0.0012 0.4387 0.9361 0.250 0.2408 0.01211 0.00646 0.0000 0.4295 0.9399 0.500 0.2555 0.01221 0.00653 0.0027 0.4228 0.9460 0.750 0.2909 0.01216 0.00638 0.0010 0.4155 0.9471 1.000 0.3256 0.01211 0.00627 -0.0005 0.4088 0.9484 1.250 0.3587 0.01209 0.00617 -0.0017 0.4021 0.9499 1.500 0.3900 0.01212 0.00612 -0.0026 0.3969 0.9519 1.750 0.4190 0.01211 0.00610 -0.0029 0.3924 0.9542 2.000 0.4424 0.01217 0.00612 -0.0021 0.3881 0.9574 2.250 0.4634 0.01226 0.00616 -0.0008 0.3841 0.9605 2.500 0.4969 0.01219 0.00606 -0.0022 0.3802 0.9615 2.750 0.5291 0.01213 0.00600 -0.0033 0.3765 0.9625 3.000 0.5603 0.01211 0.00596 -0.0042 0.3727 0.9639 3.250 0.5899 0.01215 0.00594 -0.0047 0.3689 0.9654 3.500 0.6176 0.01218 0.00597 -0.0049 0.3655 0.9670 3.750 0.6442 0.01220 0.00601 -0.0048 0.3622 0.9690 4.000 0.6669 0.01229 0.00609 -0.0040 0.3585 0.9711 4.250 0.6872 0.01243 0.00621 -0.0026 0.3554 0.9731 4.500 0.7191 0.01243 0.00619 -0.0037 0.3518 0.9740 4.750 0.7498 0.01239 0.00620 -0.0045 0.3482 0.9748 5.000 0.7784 0.01240 0.00623 -0.0050 0.3444 0.9757 5.250 0.8070 0.01249 0.00629 -0.0054 0.3402 0.9768 5.500 0.8349 0.01260 0.00640 -0.0057 0.3365 0.9780 5.750 0.8611 0.01263 0.00649 -0.0057 0.3327 0.9791 6.000 0.8862 0.01271 0.00661 -0.0054 0.3290 0.9801 6.250 0.9108 0.01288 0.00675 -0.0050 0.3245 0.9815 6.500 0.9341 0.01303 0.00695 -0.0044 0.3206 0.9827 6.750 0.9556 0.01312 0.00712 -0.0033 0.3165 0.9837 7.000 0.9784 0.01321 0.00724 -0.0026 0.3119 0.9845 7.250 1.0071 0.01337 0.00737 -0.0032 0.3064 0.9852 7.500 1.0362 0.01332 0.00745 -0.0038 0.3017 0.9860 7.750 1.0627 0.01335 0.00754 -0.0039 0.2965 0.9866 8.000 1.0876 0.01350 0.00769 -0.0037 0.2911 0.9872 8.250 1.1137 0.01348 0.00780 -0.0036 0.2853 0.9879 8.500 1.1396 0.01354 0.00790 -0.0036 0.2787 0.9887 8.750 1.1659 0.01359 0.00803 -0.0037 0.2709 0.9897 9.000 1.1895 0.01370 0.00816 -0.0032 0.2622 0.9905 9.250 1.2124 0.01384 0.00835 -0.0027 0.2526 0.9911 9.500 1.2343 0.01406 0.00860 -0.0020 0.2428 0.9919 9.750 1.2547 0.01437 0.00891 -0.0011 0.2322 0.9926 10.000 1.2740 0.01475 0.00929 0.0000 0.2208 0.9935 10.250 1.2956 0.01514 0.00970 0.0005 0.2080 0.9945 10.500 1.3175 0.01559 0.01014 0.0009 0.1934 0.9952 10.750 1.3374 0.01610 0.01065 0.0015 0.1773 0.9960 11.000 1.3557 0.01672 0.01124 0.0024 0.1617 0.9969 11.250 1.3722 0.01744 0.01193 0.0034 0.1462 0.9979 11.500 1.3868 0.01829 0.01274 0.0046 0.1303 0.9991 11.750 1.3996 0.01917 0.01360 0.0061 0.1167 1.0000 12.000 1.4001 0.01999 0.01442 0.0100 0.1062 1.0000 12.250 1.3956 0.02079 0.01525 0.0148 0.0988 1.0000 12.500 1.3772 0.02144 0.01593 0.0220 0.0940 1.0000 12.750 1.3562 0.02238 0.01689 0.0289 0.0900 1.0000 13.000 1.3406 0.02341 0.01800 0.0342 0.0865 1.0000 13.250 1.3209 0.02481 0.01946 0.0393 0.0832 1.0000 13.500 1.2996 0.02657 0.02126 0.0439 0.0800 1.0000 13.750 1.2885 0.02858 0.02332 0.0464 0.0760 1.0000 14.000 1.2795 0.03115 0.02594 0.0475 0.0714 1.0000 14.250 1.2697 0.03415 0.02898 0.0480 0.0667 1.0000 14.500 1.2614 0.03723 0.03211 0.0482 0.0622 1.0000 14.750 1.2494 0.04082 0.03576 0.0481 0.0589 1.0000 15.000 1.2408 0.04417 0.03918 0.0478 0.0552 1.0000 15.250 1.2292 0.04792 0.04298 0.0474 0.0522 1.0000 15.500 1.2148 0.05207 0.04719 0.0467 0.0496 1.0000 15.750 1.2060 0.05571 0.05091 0.0460 0.0469 1.0000 16.000 1.1958 0.05969 0.05496 0.0451 0.0446 1.0000 16.250 1.1820 0.06424 0.05954 0.0439 0.0420 1.0000 16.500 1.1721 0.06840 0.06377 0.0428 0.0401 1.0000 16.750 1.1644 0.07241 0.06786 0.0416 0.0377 1.0000 17.000 1.1529 0.07696 0.07245 0.0401 0.0356 1.0000 17.250 1.1404 0.08176 0.07730 0.0385 0.0339 1.0000 17.500 1.1359 0.08553 0.08116 0.0373 0.0322 1.0000 17.750 1.1280 0.08983 0.08552 0.0357 0.0303 1.0000 18.000 1.1169 0.09467 0.09039 0.0339 0.0288 1.0000