XFOIL Version 6.96 Calculated polar for: EPPLER 327 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 -0.4457 0.09023 0.08682 -0.0277 1.0000 0.0267 -9.500 -0.4646 0.08262 0.07919 -0.0350 1.0000 0.0269 -9.250 -0.4824 0.07788 0.07438 -0.0366 1.0000 0.0270 -9.000 -0.4964 0.07453 0.07098 -0.0360 1.0000 0.0270 -8.750 -0.5152 0.07143 0.06780 -0.0334 1.0000 0.0270 -8.500 -0.5277 0.06861 0.06490 -0.0306 1.0000 0.0270 -8.250 -0.5373 0.06554 0.06171 -0.0279 1.0000 0.0270 -7.750 -0.5548 0.05291 0.04887 -0.0215 1.0000 0.0141 -7.500 -0.5561 0.05068 0.04657 -0.0185 1.0000 0.0140 -7.250 -0.5424 0.04720 0.04290 -0.0187 0.9836 0.0136 -7.000 -0.5241 0.04297 0.03836 -0.0193 0.9386 0.0132 -6.500 -0.4772 0.03012 0.02384 -0.0192 0.8651 0.0112 -6.250 -0.4533 0.02768 0.02093 -0.0187 0.8305 0.0111 -6.000 -0.4311 0.02567 0.01847 -0.0175 0.8017 0.0111 -5.750 -0.4084 0.02382 0.01618 -0.0163 0.7761 0.0111 -5.250 -0.3591 0.02105 0.01275 -0.0145 0.7337 0.0112 -5.000 -0.3340 0.01990 0.01141 -0.0138 0.7147 0.0114 -4.750 -0.3094 0.01898 0.01034 -0.0131 0.6973 0.0118 -4.500 -0.2853 0.01821 0.00944 -0.0123 0.6809 0.0123 -4.250 -0.2619 0.01751 0.00861 -0.0113 0.6656 0.0127 -4.000 -0.2391 0.01689 0.00785 -0.0102 0.6511 0.0134 -3.750 -0.2172 0.01630 0.00713 -0.0090 0.6376 0.0145 -3.500 -0.1949 0.01589 0.00665 -0.0079 0.6246 0.0159 -3.250 -0.1723 0.01551 0.00618 -0.0068 0.6116 0.0184 -3.000 -0.1498 0.01514 0.00573 -0.0058 0.5997 0.0215 -2.750 -0.1279 0.01473 0.00524 -0.0045 0.5887 0.0275 -2.500 -0.1069 0.01428 0.00484 -0.0032 0.5778 0.0466 -2.250 -0.0870 0.01377 0.00454 -0.0018 0.5672 0.1008 -2.000 -0.0789 0.01249 0.00414 0.0014 0.5585 0.3185 -1.750 -0.0812 0.01139 0.00503 0.0089 0.5504 0.8034 -1.500 -0.0597 0.01188 0.00539 0.0113 0.5414 0.8382 -1.250 -0.0296 0.01251 0.00588 0.0121 0.5314 0.8581 -1.000 0.0052 0.01318 0.00641 0.0121 0.5215 0.8745 -0.750 0.0415 0.01375 0.00681 0.0115 0.5125 0.8876 -0.500 0.0792 0.01401 0.00693 0.0099 0.5030 0.8929 -0.250 0.0988 0.01396 0.00674 0.0115 0.4956 0.8970 0.000 0.1180 0.01387 0.00656 0.0131 0.4878 0.9006 0.250 0.1471 0.01389 0.00644 0.0128 0.4805 0.9019 0.500 0.1758 0.01389 0.00636 0.0126 0.4728 0.9034 0.750 0.2029 0.01391 0.00627 0.0126 0.4660 0.9050 1.000 0.2292 0.01391 0.00620 0.0128 0.4587 0.9070 1.250 0.2531 0.01390 0.00611 0.0134 0.4524 0.9092 1.500 0.2739 0.01389 0.00603 0.0147 0.4467 0.9123 1.750 0.2909 0.01382 0.00592 0.0167 0.4406 0.9155 2.000 0.3193 0.01388 0.00589 0.0164 0.4347 0.9166 2.250 0.3477 0.01391 0.00591 0.0162 0.4284 0.9178 2.500 0.3747 0.01396 0.00591 0.0162 0.4225 0.9191 2.750 0.4009 0.01402 0.00590 0.0163 0.4174 0.9205 3.000 0.4269 0.01405 0.00594 0.0165 0.4112 0.9221 3.250 0.4517 0.01411 0.00598 0.0169 0.4059 0.9242 3.500 0.4743 0.01417 0.00599 0.0178 0.4012 0.9265 3.750 0.4945 0.01418 0.00602 0.0191 0.3957 0.9291 4.000 0.5174 0.01423 0.00606 0.0198 0.3907 0.9310 4.250 0.5452 0.01434 0.00614 0.0196 0.3858 0.9321 4.500 0.5733 0.01443 0.00629 0.0193 0.3800 0.9335 4.750 0.6004 0.01455 0.00639 0.0192 0.3749 0.9350 5.000 0.6265 0.01467 0.00651 0.0193 0.3702 0.9366 5.250 0.6518 0.01476 0.00667 0.0195 0.3645 0.9384 5.500 0.6757 0.01487 0.00679 0.0200 0.3596 0.9405 5.750 0.6979 0.01499 0.00692 0.0208 0.3549 0.9430 6.000 0.7195 0.01508 0.00709 0.0218 0.3494 0.9455 6.250 0.7476 0.01524 0.00727 0.0214 0.3440 0.9468 6.500 0.7755 0.01541 0.00749 0.0210 0.3386 0.9484 6.750 0.8026 0.01557 0.00774 0.0208 0.3323 0.9502 7.000 0.8282 0.01575 0.00792 0.0209 0.3270 0.9522 7.250 0.8530 0.01591 0.00819 0.0211 0.3205 0.9545 7.500 0.8756 0.01607 0.00841 0.0217 0.3144 0.9573 7.750 0.8987 0.01625 0.00865 0.0222 0.3083 0.9599 8.000 0.9267 0.01646 0.00896 0.0217 0.3008 0.9615 8.250 0.9536 0.01670 0.00927 0.0213 0.2938 0.9634 8.500 0.9798 0.01693 0.00959 0.0211 0.2856 0.9657 8.750 1.0046 0.01719 0.00993 0.0211 0.2778 0.9687 9.000 1.0266 0.01745 0.01027 0.0217 0.2692 0.9726 9.250 1.0547 0.01777 0.01069 0.0209 0.2595 0.9745 9.500 1.0809 0.01813 0.01112 0.0204 0.2495 0.9770 9.750 1.1053 0.01854 0.01158 0.0202 0.2384 0.9802 10.250 1.1539 0.01949 0.01270 0.0195 0.2135 0.9867 10.500 1.1772 0.02010 0.01337 0.0191 0.1996 0.9907 10.750 1.1980 0.02083 0.01413 0.0189 0.1850 0.9960 11.000 1.2066 0.02148 0.01483 0.0211 0.1729 1.0000 11.250 1.1928 0.02189 0.01523 0.0277 0.1667 1.0000 11.500 1.1900 0.02263 0.01598 0.0317 0.1569 1.0000 11.750 1.1913 0.02359 0.01696 0.0345 0.1467 1.0000 12.000 1.1917 0.02482 0.01820 0.0368 0.1366 1.0000 12.250 1.1907 0.02635 0.01975 0.0387 0.1275 1.0000 12.500 1.1899 0.02811 0.02154 0.0399 0.1182 1.0000 12.750 1.1887 0.03013 0.02362 0.0408 0.1098 1.0000 13.000 1.1847 0.03258 0.02610 0.0413 0.1027 1.0000 13.250 1.1824 0.03506 0.02865 0.0414 0.0953 1.0000 13.500 1.1775 0.03793 0.03157 0.0413 0.0896 1.0000 13.750 1.1734 0.04085 0.03456 0.0410 0.0839 1.0000 14.000 1.1658 0.04425 0.03800 0.0404 0.0792 1.0000 14.250 1.1618 0.04733 0.04119 0.0399 0.0746 1.0000 14.500 1.1526 0.05109 0.04500 0.0390 0.0702 1.0000 14.750 1.1460 0.05463 0.04861 0.0381 0.0668 1.0000 15.000 1.1391 0.05829 0.05236 0.0371 0.0627 1.0000 15.250 1.1299 0.06241 0.05653 0.0358 0.0598 1.0000 15.500 1.1237 0.06627 0.06049 0.0345 0.0567 1.0000 15.750 1.1173 0.07025 0.06456 0.0332 0.0534 1.0000 16.000 1.1084 0.07468 0.06904 0.0315 0.0507 1.0000 16.250 1.1015 0.07895 0.07338 0.0298 0.0483 1.0000 16.500 1.0963 0.08305 0.07759 0.0282 0.0454 1.0000 16.750 1.0893 0.08751 0.08212 0.0264 0.0432 1.0000 17.250 1.0760 0.09655 0.09132 0.0225 0.0390 1.0000 17.500 1.0706 0.10100 0.09585 0.0205 0.0370 1.0000 17.750 1.0637 0.10578 0.10069 0.0183 0.0353 1.0000