XFOIL Version 6.96 Calculated polar for: EPPLER 340 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.5350 0.09256 0.08949 -0.0023 1.0000 0.0264 -9.250 -0.5909 0.07206 0.06871 -0.0136 1.0000 0.0176 -8.750 -0.6233 0.06198 0.05835 -0.0097 1.0000 0.0141 -8.500 -0.6272 0.05939 0.05568 -0.0076 1.0000 0.0140 -8.250 -0.6244 0.05623 0.05232 -0.0066 0.8920 0.0138 -8.000 -0.6262 0.05333 0.04907 -0.0034 0.8252 0.0136 -7.750 -0.6257 0.05013 0.04554 -0.0004 0.7894 0.0133 -7.500 -0.6235 0.04655 0.04159 0.0027 0.7632 0.0129 -7.250 -0.6198 0.04249 0.03709 0.0060 0.7424 0.0125 -6.750 -0.6073 0.03171 0.02470 0.0143 0.7104 0.0112 -6.500 -0.5894 0.02952 0.02209 0.0161 0.6927 0.0112 -6.250 -0.5688 0.02751 0.01966 0.0176 0.6759 0.0112 -6.000 -0.5457 0.02574 0.01750 0.0187 0.6599 0.0112 -5.750 -0.5207 0.02419 0.01565 0.0194 0.6445 0.0113 -5.500 -0.4950 0.02287 0.01413 0.0199 0.6299 0.0115 -5.250 -0.4688 0.02178 0.01286 0.0203 0.6159 0.0117 -5.000 -0.4424 0.02081 0.01173 0.0207 0.6027 0.0121 -4.500 -0.3906 0.01913 0.00977 0.0217 0.5788 0.0130 -4.250 -0.3658 0.01840 0.00890 0.0224 0.5677 0.0137 -4.000 -0.3419 0.01776 0.00815 0.0232 0.5570 0.0145 -3.750 -0.3176 0.01725 0.00760 0.0239 0.5462 0.0159 -3.500 -0.2935 0.01682 0.00707 0.0247 0.5365 0.0183 -3.250 -0.2694 0.01642 0.00659 0.0255 0.5270 0.0213 -3.000 -0.2455 0.01598 0.00608 0.0263 0.5187 0.0253 -2.750 -0.2218 0.01556 0.00567 0.0272 0.5100 0.0349 -2.500 -0.1992 0.01508 0.00527 0.0282 0.5021 0.0609 -2.250 -0.1782 0.01451 0.00496 0.0293 0.4938 0.1254 -2.000 -0.1220 0.01335 0.00682 0.0259 0.4842 0.8255 -1.750 -0.1078 0.01382 0.00716 0.0294 0.4775 0.8622 -1.500 -0.0892 0.01439 0.00757 0.0321 0.4716 0.8838 -1.250 -0.0506 0.01515 0.00819 0.0310 0.4636 0.8992 -1.000 -0.0104 0.01588 0.00871 0.0295 0.4564 0.9135 -0.750 0.0390 0.01618 0.00886 0.0257 0.4481 0.9188 -0.500 0.0693 0.01620 0.00873 0.0252 0.4421 0.9222 -0.250 0.0913 0.01622 0.00864 0.0262 0.4372 0.9269 0.000 0.1208 0.01618 0.00851 0.0258 0.4313 0.9292 0.250 0.1532 0.01616 0.00837 0.0247 0.4256 0.9308 0.500 0.1844 0.01615 0.00825 0.0239 0.4204 0.9326 0.750 0.2142 0.01614 0.00817 0.0234 0.4149 0.9348 1.000 0.2416 0.01615 0.00810 0.0233 0.4103 0.9373 1.250 0.2643 0.01621 0.00805 0.0241 0.4063 0.9406 1.500 0.2919 0.01619 0.00802 0.0240 0.4013 0.9424 1.750 0.3233 0.01617 0.00795 0.0231 0.3964 0.9436 2.000 0.3537 0.01619 0.00789 0.0224 0.3923 0.9450 2.250 0.3828 0.01622 0.00787 0.0219 0.3886 0.9464 2.500 0.4111 0.01624 0.00789 0.0216 0.3843 0.9482 2.750 0.4377 0.01628 0.00791 0.0216 0.3801 0.9502 3.000 0.4618 0.01634 0.00792 0.0221 0.3763 0.9521 3.250 0.4864 0.01642 0.00797 0.0225 0.3728 0.9540 3.500 0.5169 0.01644 0.00802 0.0217 0.3684 0.9550 3.750 0.5460 0.01647 0.00806 0.0212 0.3643 0.9559 4.000 0.5745 0.01654 0.00811 0.0208 0.3607 0.9570 4.250 0.6026 0.01664 0.00817 0.0205 0.3577 0.9584 4.500 0.6295 0.01671 0.00830 0.0204 0.3538 0.9597 4.750 0.6549 0.01679 0.00842 0.0205 0.3498 0.9609 5.000 0.6790 0.01690 0.00855 0.0210 0.3461 0.9625 5.250 0.7029 0.01704 0.00866 0.0215 0.3429 0.9641 5.500 0.7312 0.01713 0.00882 0.0211 0.3390 0.9648 5.750 0.7588 0.01723 0.00900 0.0208 0.3350 0.9655 6.000 0.7860 0.01733 0.00915 0.0206 0.3312 0.9663 6.250 0.8133 0.01747 0.00928 0.0203 0.3276 0.9673 6.500 0.8399 0.01762 0.00951 0.0202 0.3237 0.9685 6.750 0.8648 0.01776 0.00976 0.0204 0.3193 0.9695 7.000 0.8887 0.01790 0.00996 0.0208 0.3150 0.9705 7.250 0.9116 0.01808 0.01014 0.0214 0.3113 0.9715 7.500 0.9340 0.01827 0.01045 0.0221 0.3068 0.9730 7.750 0.9612 0.01842 0.01071 0.0217 0.3018 0.9737 8.000 0.9866 0.01858 0.01091 0.0217 0.2971 0.9744 8.250 1.0113 0.01878 0.01121 0.0218 0.2920 0.9752 8.500 1.0355 0.01897 0.01152 0.0221 0.2862 0.9760 8.750 1.0587 0.01917 0.01177 0.0225 0.2812 0.9769 9.000 1.0817 0.01941 0.01215 0.0228 0.2753 0.9779 9.250 1.1039 0.01964 0.01247 0.0234 0.2686 0.9794 9.500 1.1235 0.01991 0.01283 0.0244 0.2623 0.9805 9.750 1.1449 0.02018 0.01322 0.0250 0.2549 0.9814 10.000 1.1669 0.02049 0.01360 0.0254 0.2475 0.9822 10.250 1.1877 0.02082 0.01404 0.0259 0.2387 0.9832 10.500 1.2072 0.02122 0.01454 0.0267 0.2298 0.9843 10.750 1.2240 0.02169 0.01506 0.0278 0.2210 0.9856 11.000 1.2403 0.02222 0.01569 0.0289 0.2106 0.9874 11.250 1.2565 0.02284 0.01638 0.0299 0.1997 0.9889 11.500 1.2707 0.02357 0.01717 0.0309 0.1886 0.9904 11.750 1.2808 0.02444 0.01809 0.0324 0.1775 0.9923 12.000 1.2861 0.02547 0.01916 0.0344 0.1666 0.9945 12.250 1.2891 0.02658 0.02034 0.0363 0.1559 0.9966 12.500 1.2878 0.02812 0.02195 0.0377 0.1465 0.9992 12.750 1.2724 0.03000 0.02387 0.0409 0.1405 1.0000 13.000 1.2551 0.03204 0.02599 0.0442 0.1356 1.0000 13.250 1.2378 0.03438 0.02839 0.0469 0.1304 1.0000 13.500 1.2177 0.03713 0.03118 0.0492 0.1261 1.0000 13.750 1.2018 0.03975 0.03387 0.0512 0.1212 1.0000 14.000 1.1838 0.04276 0.03693 0.0527 0.1166 1.0000 14.250 1.1647 0.04614 0.04034 0.0538 0.1126 1.0000 14.500 1.1516 0.04932 0.04359 0.0543 0.1075 1.0000 14.750 1.1366 0.05306 0.04736 0.0541 0.1029 1.0000 15.000 1.1235 0.05687 0.05122 0.0536 0.0985 1.0000 15.250 1.1128 0.06069 0.05511 0.0527 0.0935 1.0000 15.500 1.0996 0.06503 0.05946 0.0515 0.0893 1.0000 15.750 1.0922 0.06883 0.06335 0.0503 0.0846 1.0000 16.000 1.0824 0.07305 0.06761 0.0489 0.0802 1.0000 16.250 1.0731 0.07728 0.07189 0.0475 0.0764 1.0000 16.500 1.0666 0.08126 0.07594 0.0461 0.0722 1.0000 16.750 1.0574 0.08568 0.08039 0.0444 0.0686 1.0000 17.000 1.0506 0.08981 0.08458 0.0429 0.0651 1.0000