E195 (11.82%) (e195-il) Xfoil prediction polar at RE=200,000 Ncrit=5
Details | Polar file |
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Airfoil: E195 (11.82%) (e195-il) Reynolds number: 200,000 Max Cl/Cd: 78.22 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e195-il-200000-n5.txt Download as CSV file: xf-e195-il-200000-n5.csv |
XFOIL Version 6.96 Calculated polar for: E195 (11.82%) 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 ------ -------- --------- --------- -------- -------- -------- -10.000 -0.4035 0.08812 0.08458 -0.0431 1.0000 0.0179 -9.750 -0.4107 0.08288 0.07940 -0.0454 1.0000 0.0175 -9.500 -0.4208 0.07719 0.07377 -0.0481 1.0000 0.0176 -9.250 -0.4375 0.07031 0.06698 -0.0517 1.0000 0.0175 -9.000 -0.5087 0.05338 0.05004 -0.0628 1.0000 0.0161 -8.500 -0.5165 0.04014 0.03600 -0.0727 0.9716 0.0165 -8.250 -0.5023 0.03576 0.03115 -0.0751 0.9547 0.0168 -8.000 -0.4845 0.03191 0.02677 -0.0766 0.9378 0.0170 -7.750 -0.4629 0.02859 0.02292 -0.0777 0.9218 0.0171 -7.500 -0.4385 0.02600 0.01987 -0.0783 0.9061 0.0172 -7.250 -0.4132 0.02398 0.01746 -0.0786 0.8903 0.0175 -7.000 -0.3881 0.02234 0.01549 -0.0786 0.8744 0.0177 -6.750 -0.3633 0.02097 0.01384 -0.0783 0.8589 0.0181 -6.500 -0.3391 0.01982 0.01243 -0.0778 0.8440 0.0185 -6.250 -0.3150 0.01883 0.01124 -0.0771 0.8301 0.0189 -6.000 -0.2910 0.01799 0.01020 -0.0765 0.8169 0.0194 -5.750 -0.2672 0.01721 0.00927 -0.0758 0.8046 0.0201 -5.500 -0.2437 0.01647 0.00844 -0.0752 0.7934 0.0215 -5.250 -0.2193 0.01593 0.00777 -0.0747 0.7827 0.0228 -5.000 -0.1946 0.01539 0.00710 -0.0741 0.7725 0.0239 -4.750 -0.1696 0.01491 0.00647 -0.0736 0.7633 0.0251 -4.500 -0.1443 0.01446 0.00589 -0.0731 0.7542 0.0269 -4.250 -0.1188 0.01404 0.00538 -0.0727 0.7459 0.0306 -4.000 -0.0932 0.01363 0.00492 -0.0723 0.7380 0.0401 -3.750 -0.0680 0.01316 0.00455 -0.0719 0.7302 0.0697 -3.500 -0.0427 0.01276 0.00425 -0.0716 0.7232 0.1111 -3.250 -0.0172 0.01238 0.00402 -0.0714 0.7161 0.1580 -3.000 0.0083 0.01204 0.00381 -0.0711 0.7094 0.2112 -2.750 0.0333 0.01163 0.00366 -0.0708 0.7031 0.2866 -2.500 0.0583 0.01130 0.00355 -0.0705 0.6967 0.3619 -2.250 0.0838 0.01108 0.00346 -0.0701 0.6911 0.4255 -2.000 0.1095 0.01089 0.00341 -0.0696 0.6848 0.4810 -1.750 0.1354 0.01077 0.00334 -0.0692 0.6794 0.5252 -1.500 0.1614 0.01065 0.00329 -0.0688 0.6737 0.5657 -1.250 0.1872 0.01053 0.00326 -0.0683 0.6680 0.6066 -1.000 0.2128 0.01043 0.00323 -0.0676 0.6633 0.6493 -0.750 0.2382 0.01031 0.00323 -0.0670 0.6576 0.6945 -0.500 0.2633 0.01020 0.00324 -0.0662 0.6523 0.7433 -0.250 0.2889 0.01012 0.00325 -0.0653 0.6480 0.7967 0.000 0.3179 0.01005 0.00331 -0.0651 0.6423 0.8545 0.250 0.3565 0.01006 0.00333 -0.0670 0.6372 0.9076 0.500 0.3985 0.01011 0.00331 -0.0699 0.6327 0.9471 0.750 0.4386 0.01016 0.00333 -0.0725 0.6269 0.9744 1.000 0.4801 0.01021 0.00332 -0.0755 0.6218 0.9920 1.250 0.5139 0.01029 0.00333 -0.0769 0.6172 1.0000 1.500 0.5380 0.01038 0.00340 -0.0763 0.6117 1.0000 1.750 0.5625 0.01048 0.00346 -0.0757 0.6069 1.0000 2.000 0.5871 0.01060 0.00353 -0.0751 0.6024 1.0000 2.250 0.6117 0.01071 0.00365 -0.0745 0.5968 1.0000 2.500 0.6365 0.01083 0.00374 -0.0740 0.5919 1.0000 2.750 0.6615 0.01095 0.00385 -0.0735 0.5871 1.0000 3.000 0.6864 0.01107 0.00401 -0.0729 0.5813 1.0000 3.250 0.7117 0.01120 0.00411 -0.0724 0.5762 1.0000 3.500 0.7367 0.01133 0.00427 -0.0719 0.5699 1.0000 3.750 0.7618 0.01145 0.00441 -0.0714 0.5634 1.0000 4.000 0.7868 0.01158 0.00457 -0.0709 0.5565 1.0000 4.250 0.8118 0.01170 0.00471 -0.0703 0.5485 1.0000 4.500 0.8366 0.01183 0.00487 -0.0698 0.5401 1.0000 4.750 0.8615 0.01196 0.00500 -0.0692 0.5318 1.0000 5.000 0.8860 0.01208 0.00521 -0.0686 0.5216 1.0000 5.250 0.9105 0.01222 0.00539 -0.0680 0.5113 1.0000 5.500 0.9348 0.01237 0.00556 -0.0673 0.5002 1.0000 5.750 0.9586 0.01253 0.00575 -0.0666 0.4879 1.0000 6.000 0.9822 0.01271 0.00598 -0.0658 0.4738 1.0000 6.250 1.0053 0.01291 0.00623 -0.0649 0.4576 1.0000 6.500 1.0278 0.01314 0.00649 -0.0640 0.4389 1.0000 6.750 1.0488 0.01344 0.00676 -0.0628 0.4151 1.0000 7.000 1.0673 0.01386 0.00710 -0.0613 0.3784 1.0000 7.250 1.0813 0.01454 0.00754 -0.0591 0.3284 1.0000 7.500 1.0905 0.01554 0.00821 -0.0563 0.2689 1.0000 7.750 1.0975 0.01671 0.00904 -0.0534 0.2130 1.0000 8.000 1.1069 0.01773 0.00986 -0.0509 0.1739 1.0000 8.250 1.1161 0.01871 0.01069 -0.0483 0.1411 1.0000 8.500 1.1230 0.01972 0.01156 -0.0455 0.1127 1.0000 8.750 1.1281 0.02074 0.01246 -0.0424 0.0888 1.0000 9.000 1.1319 0.02191 0.01348 -0.0393 0.0657 1.0000 9.250 1.1379 0.02302 0.01453 -0.0368 0.0501 1.0000 9.500 1.1433 0.02424 0.01571 -0.0344 0.0376 1.0000 9.750 1.1482 0.02559 0.01704 -0.0321 0.0272 1.0000 10.000 1.1523 0.02709 0.01855 -0.0301 0.0202 1.0000 10.250 1.1577 0.02859 0.02009 -0.0283 0.0172 1.0000 10.500 1.1633 0.03016 0.02177 -0.0267 0.0156 1.0000 10.750 1.1691 0.03178 0.02349 -0.0253 0.0143 1.0000 11.000 1.1743 0.03352 0.02532 -0.0241 0.0135 1.0000 11.250 1.1778 0.03548 0.02737 -0.0230 0.0127 1.0000 11.500 1.1821 0.03743 0.02942 -0.0220 0.0120 1.0000 11.750 1.1863 0.03945 0.03157 -0.0212 0.0116 1.0000 12.000 1.1903 0.04153 0.03376 -0.0205 0.0110 1.0000 12.250 1.1931 0.04381 0.03616 -0.0198 0.0107 1.0000 12.500 1.1942 0.04629 0.03875 -0.0193 0.0103 1.0000 12.750 1.1960 0.04877 0.04135 -0.0189 0.0101 1.0000 13.000 1.1968 0.05142 0.04413 -0.0186 0.0100 1.0000 13.250 1.1965 0.05426 0.04707 -0.0184 0.0097 1.0000 13.500 1.1947 0.05736 0.05027 -0.0183 0.0094 1.0000 13.750 1.1956 0.06022 0.05325 -0.0183 0.0094 1.0000 14.000 1.1938 0.06349 0.05661 -0.0184 0.0092 1.0000 14.250 1.1915 0.06688 0.06010 -0.0186 0.0090 1.0000 14.500 1.1926 0.06996 0.06330 -0.0188 0.0090 1.0000 14.750 1.1935 0.07315 0.06664 -0.0192 0.0089 1.0000 15.000 1.1939 0.07648 0.07011 -0.0197 0.0089 1.0000 15.250 1.1931 0.08012 0.07391 -0.0203 0.0087 1.0000 15.500 1.1919 0.08385 0.07780 -0.0211 0.0087 1.0000 15.750 1.1901 0.08777 0.08188 -0.0222 0.0086 1.0000 16.000 1.1871 0.09200 0.08629 -0.0234 0.0086 1.0000 16.250 1.1827 0.09658 0.09107 -0.0250 0.0085 1.0000 16.500 1.1767 0.10154 0.09622 -0.0269 0.0085 1.0000 16.750 1.1696 0.10687 0.10174 -0.0291 0.0085 1.0000 17.000 1.1609 0.11268 0.10774 -0.0319 0.0084 1.0000 17.250 1.1520 0.11869 0.11392 -0.0349 0.0084 1.0000 17.500 1.1406 0.12546 0.12089 -0.0386 0.0084 1.0000 17.750 1.1290 0.13246 0.12808 -0.0425 0.0084 1.0000 18.000 1.1160 0.14013 0.13593 -0.0471 0.0084 1.0000 18.250 1.1021 0.14837 0.14435 -0.0522 0.0084 1.0000 18.500 1.0877 0.15710 0.15324 -0.0577 0.0085 1.0000 18.750 1.0690 0.16762 0.16392 -0.0643 0.0086 1.0000 19.000 1.0502 0.17876 0.17518 -0.0712 0.0087 1.0000 |
Polar data table (+)
Polar graphs
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