GOE 431 AIRFOIL (goe431-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 431 AIRFOIL (goe431-il) Reynolds number: 200,000 Max Cl/Cd: 72.45 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe431-il-200000-n5.txt Download as CSV file: xf-goe431-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 431 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0612 0.09137 0.08748 -0.1123 0.9293 0.0181
-10.250 -0.0567 0.08513 0.08123 -0.1171 0.9248 0.0185
-9.750 -0.1377 0.05511 0.05093 -0.1405 0.9038 0.0174
-9.500 -0.1541 0.04979 0.04548 -0.1444 0.8928 0.0172
-9.250 -0.1603 0.04459 0.04012 -0.1504 0.8840 0.0174
-9.000 -0.1534 0.03959 0.03491 -0.1580 0.8775 0.0177
-8.750 -0.1374 0.03495 0.03004 -0.1659 0.8724 0.0182
-8.500 -0.1161 0.03137 0.02626 -0.1721 0.8675 0.0186
-8.250 -0.0870 0.02813 0.02273 -0.1785 0.8641 0.0194
-8.000 -0.0546 0.02553 0.01994 -0.1840 0.8617 0.0202
-7.750 -0.0208 0.02334 0.01758 -0.1891 0.8597 0.0217
-7.500 0.0059 0.02203 0.01612 -0.1912 0.8564 0.0235
-7.250 0.0345 0.02094 0.01485 -0.1930 0.8534 0.0255
-7.000 0.0647 0.01972 0.01349 -0.1952 0.8508 0.0280
-6.750 0.0953 0.01879 0.01235 -0.1969 0.8486 0.0316
-6.500 0.1265 0.01774 0.01115 -0.1987 0.8468 0.0378
-6.250 0.1585 0.01676 0.00997 -0.2005 0.8449 0.0470
-6.000 0.1844 0.01599 0.00906 -0.2008 0.8411 0.0588
-5.750 0.2122 0.01519 0.00828 -0.2015 0.8373 0.0825
-5.500 0.2416 0.01538 0.00853 -0.2017 0.8337 0.1256
-5.250 0.2724 0.01568 0.00866 -0.2019 0.8307 0.1412
-5.000 0.3004 0.01586 0.00863 -0.2018 0.8273 0.1504
-4.750 0.3257 0.01594 0.00870 -0.2012 0.8230 0.1549
-4.500 0.3538 0.01595 0.00861 -0.2012 0.8194 0.1603
-4.250 0.3837 0.01585 0.00827 -0.2015 0.8162 0.1642
-4.000 0.4132 0.01563 0.00798 -0.2018 0.8131 0.1678
-3.750 0.4372 0.01561 0.00798 -0.2010 0.8082 0.1712
-3.500 0.4646 0.01548 0.00777 -0.2008 0.8039 0.1743
-3.250 0.4942 0.01529 0.00745 -0.2010 0.8002 0.1769
-3.000 0.5228 0.01509 0.00713 -0.2011 0.7968 0.1782
-2.750 0.5477 0.01496 0.00693 -0.2005 0.7924 0.1790
-2.500 0.5748 0.01479 0.00669 -0.2002 0.7885 0.1797
-2.250 0.6037 0.01461 0.00642 -0.2003 0.7849 0.1805
-2.000 0.6324 0.01445 0.00618 -0.2003 0.7812 0.1813
-1.750 0.6564 0.01432 0.00607 -0.1995 0.7759 0.1823
-1.500 0.6834 0.01415 0.00590 -0.1993 0.7712 0.1834
-1.250 0.7133 0.01396 0.00567 -0.1995 0.7668 0.1847
-1.000 0.7364 0.01391 0.00566 -0.1985 0.7604 0.1862
-0.750 0.7629 0.01381 0.00556 -0.1981 0.7548 0.1882
-0.500 0.7907 0.01369 0.00543 -0.1979 0.7493 0.1903
-0.250 0.8144 0.01365 0.00541 -0.1970 0.7413 0.1923
0.000 0.8418 0.01353 0.00527 -0.1967 0.7341 0.1943
0.250 0.8652 0.01350 0.00527 -0.1957 0.7250 0.1962
0.500 0.8899 0.01343 0.00521 -0.1949 0.7148 0.1984
0.750 0.9140 0.01335 0.00516 -0.1940 0.7013 0.2012
1.000 0.9370 0.01331 0.00513 -0.1929 0.6824 0.2044
1.250 0.9599 0.01325 0.00498 -0.1916 0.6439 0.2084
1.500 0.9665 0.01383 0.00478 -0.1869 0.5278 0.2117
1.750 0.9762 0.01447 0.00516 -0.1834 0.4882 0.2158
2.000 0.9915 0.01492 0.00550 -0.1810 0.4644 0.2217
2.250 1.0086 0.01531 0.00580 -0.1790 0.4474 0.2296
2.500 1.0260 0.01563 0.00610 -0.1771 0.4343 0.2410
2.750 1.0438 0.01595 0.00641 -0.1752 0.4236 0.2576
3.000 1.0634 0.01622 0.00673 -0.1737 0.4145 0.2796
3.500 1.1039 0.01679 0.00740 -0.1711 0.4002 0.3393
3.750 1.1242 0.01709 0.00779 -0.1698 0.3945 0.3779
4.000 1.1462 0.01735 0.00818 -0.1689 0.3895 0.4256
4.250 1.1680 0.01763 0.00856 -0.1679 0.3847 0.4718
4.500 1.1892 0.01796 0.00895 -0.1667 0.3805 0.5089
4.750 1.2104 0.01833 0.00933 -0.1656 0.3768 0.5395
5.000 1.2331 0.01859 0.00968 -0.1648 0.3731 0.5681
5.250 1.2553 0.01886 0.01005 -0.1639 0.3694 0.5989
5.750 1.2946 0.01907 0.01074 -0.1610 0.3620 1.0000
6.000 1.3166 0.01944 0.01113 -0.1601 0.3582 1.0000
6.250 1.3382 0.01980 0.01154 -0.1592 0.3542 1.0000
6.500 1.3594 0.02020 0.01196 -0.1582 0.3504 1.0000
6.750 1.3803 0.02065 0.01240 -0.1571 0.3468 1.0000
7.000 1.4022 0.02109 0.01284 -0.1563 0.3438 1.0000
7.250 1.4244 0.02146 0.01332 -0.1554 0.3411 1.0000
7.500 1.4461 0.02186 0.01380 -0.1546 0.3383 1.0000
7.750 1.4666 0.02229 0.01430 -0.1535 0.3348 1.0000
8.000 1.4865 0.02277 0.01481 -0.1524 0.3310 1.0000
8.250 1.5069 0.02327 0.01535 -0.1514 0.3274 1.0000
8.500 1.5248 0.02372 0.01595 -0.1499 0.3227 1.0000
8.750 1.5405 0.02426 0.01656 -0.1482 0.3167 1.0000
9.000 1.5545 0.02488 0.01722 -0.1463 0.3095 1.0000
9.250 1.5669 0.02551 0.01795 -0.1442 0.3006 1.0000
9.500 1.5794 0.02620 0.01872 -0.1423 0.2916 1.0000
9.750 1.5894 0.02703 0.01959 -0.1400 0.2803 1.0000
10.000 1.6001 0.02786 0.02050 -0.1379 0.2659 1.0000
10.250 1.6114 0.02874 0.02145 -0.1360 0.2452 1.0000
10.500 1.6133 0.03027 0.02280 -0.1332 0.2029 1.0000
10.750 1.6068 0.03269 0.02489 -0.1299 0.1638 1.0000
11.000 1.6055 0.03494 0.02700 -0.1271 0.1400 1.0000
11.250 1.6049 0.03720 0.02916 -0.1247 0.1132 1.0000
11.500 1.5956 0.04030 0.03201 -0.1217 0.0705 1.0000
11.750 1.5799 0.04415 0.03561 -0.1186 0.0392 1.0000
12.000 1.5750 0.04712 0.03860 -0.1164 0.0295 1.0000
12.250 1.5742 0.04979 0.04136 -0.1147 0.0251 1.0000
12.500 1.5723 0.05268 0.04433 -0.1131 0.0221 1.0000
12.750 1.5722 0.05546 0.04724 -0.1117 0.0203 1.0000
13.000 1.5716 0.05840 0.05032 -0.1106 0.0189 1.0000
13.250 1.5688 0.06171 0.05377 -0.1095 0.0178 1.0000
13.500 1.5636 0.06547 0.05766 -0.1087 0.0170 1.0000
13.750 1.5552 0.06983 0.06218 -0.1082 0.0163 1.0000
14.000 1.5508 0.07383 0.06635 -0.1080 0.0158 1.0000
14.250 1.5448 0.07822 0.07092 -0.1081 0.0153 1.0000
14.500 1.5379 0.08296 0.07583 -0.1086 0.0148 1.0000
14.750 1.5302 0.08802 0.08105 -0.1094 0.0143 1.0000
15.000 1.5221 0.09330 0.08650 -0.1105 0.0139 1.0000
15.250 1.5138 0.09873 0.09208 -0.1119 0.0135 1.0000
15.500 1.5052 0.10429 0.09777 -0.1135 0.0132 1.0000
15.750 1.4965 0.10992 0.10353 -0.1153 0.0129 1.0000
16.000 1.4876 0.11556 0.10928 -0.1172 0.0126 1.0000
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