GOE 500 AIRFOIL (goe500-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 500 AIRFOIL (goe500-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.63 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe500-il-1000000-n5.txt Download as CSV file: xf-goe500-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 500 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2921 0.06076 0.05859 -0.1185 0.9378 0.0091
-10.750 -0.3642 0.04774 0.04536 -0.1277 0.9133 0.0088
-10.500 -0.4196 0.02502 0.02205 -0.1555 0.8943 0.0086
-10.250 -0.3986 0.02189 0.01866 -0.1596 0.8901 0.0087
-10.000 -0.3751 0.02021 0.01679 -0.1614 0.8867 0.0089
-9.750 -0.3507 0.01889 0.01532 -0.1626 0.8832 0.0091
-9.500 -0.3256 0.01779 0.01408 -0.1635 0.8797 0.0093
-9.250 -0.3002 0.01679 0.01293 -0.1642 0.8763 0.0095
-9.000 -0.2744 0.01583 0.01181 -0.1648 0.8733 0.0097
-8.750 -0.2481 0.01499 0.01083 -0.1653 0.8699 0.0099
-8.500 -0.2214 0.01429 0.01002 -0.1656 0.8662 0.0101
-8.250 -0.1946 0.01364 0.00925 -0.1659 0.8626 0.0102
-8.000 -0.1676 0.01309 0.00858 -0.1661 0.8593 0.0104
-7.750 -0.1402 0.01258 0.00799 -0.1664 0.8556 0.0105
-7.500 -0.1128 0.01211 0.00742 -0.1666 0.8515 0.0106
-7.250 -0.0856 0.01144 0.00663 -0.1668 0.8475 0.0108
-7.000 -0.0582 0.01082 0.00589 -0.1670 0.8435 0.0111
-6.750 -0.0306 0.01036 0.00535 -0.1672 0.8385 0.0114
-6.500 -0.0029 0.00998 0.00489 -0.1673 0.8330 0.0118
-6.250 0.0248 0.00967 0.00450 -0.1673 0.8267 0.0121
-6.000 0.0525 0.00937 0.00413 -0.1673 0.8187 0.0125
-5.750 0.0803 0.00911 0.00380 -0.1673 0.8107 0.0129
-5.500 0.1078 0.00890 0.00350 -0.1672 0.8016 0.0135
-5.250 0.1356 0.00871 0.00323 -0.1671 0.7913 0.0139
-5.000 0.1631 0.00854 0.00298 -0.1670 0.7800 0.0143
-4.750 0.1904 0.00836 0.00269 -0.1669 0.7681 0.0149
-4.500 0.2178 0.00819 0.00244 -0.1667 0.7564 0.0158
-4.250 0.2454 0.00805 0.00223 -0.1666 0.7463 0.0168
-4.000 0.2732 0.00793 0.00205 -0.1665 0.7378 0.0182
-3.750 0.3008 0.00781 0.00188 -0.1664 0.7295 0.0220
-3.500 0.3285 0.00761 0.00173 -0.1664 0.7214 0.0387
-3.250 0.3560 0.00752 0.00162 -0.1663 0.7132 0.0480
-3.000 0.3839 0.00746 0.00153 -0.1663 0.7048 0.0536
-2.750 0.4115 0.00740 0.00146 -0.1662 0.6970 0.0607
-2.500 0.4393 0.00733 0.00140 -0.1661 0.6895 0.0713
-2.250 0.4669 0.00730 0.00138 -0.1660 0.6826 0.0832
-2.000 0.4948 0.00728 0.00135 -0.1660 0.6753 0.0900
-1.750 0.5224 0.00729 0.00133 -0.1658 0.6679 0.0968
-1.500 0.5501 0.00729 0.00131 -0.1657 0.6599 0.1022
-1.250 0.5776 0.00729 0.00129 -0.1656 0.6519 0.1062
-1.000 0.6052 0.00730 0.00127 -0.1655 0.6436 0.1093
-0.750 0.6326 0.00733 0.00126 -0.1653 0.6362 0.1120
-0.500 0.6602 0.00734 0.00126 -0.1652 0.6281 0.1165
-0.250 0.6875 0.00735 0.00127 -0.1651 0.6204 0.1225
0.000 0.7148 0.00738 0.00128 -0.1649 0.6118 0.1272
0.250 0.7421 0.00740 0.00130 -0.1647 0.6032 0.1366
0.500 0.7689 0.00739 0.00134 -0.1645 0.5935 0.1672
0.750 0.7959 0.00735 0.00139 -0.1644 0.5830 0.2188
1.000 0.8227 0.00739 0.00146 -0.1642 0.5729 0.2437
1.250 0.8491 0.00747 0.00153 -0.1639 0.5599 0.2636
1.500 0.8741 0.00763 0.00163 -0.1633 0.5371 0.2814
1.750 0.8993 0.00778 0.00174 -0.1628 0.5158 0.3019
2.000 0.9248 0.00792 0.00185 -0.1624 0.4988 0.3194
2.250 0.9495 0.00811 0.00198 -0.1618 0.4780 0.3402
2.500 0.9737 0.00832 0.00215 -0.1611 0.4543 0.3663
2.750 0.9987 0.00847 0.00230 -0.1606 0.4386 0.3986
3.000 1.0239 0.00860 0.00246 -0.1601 0.4259 0.4366
3.250 1.0490 0.00873 0.00263 -0.1597 0.4136 0.4787
3.500 1.0736 0.00890 0.00281 -0.1591 0.3977 0.5137
3.750 1.0976 0.00910 0.00300 -0.1584 0.3778 0.5501
4.000 1.1207 0.00932 0.00324 -0.1576 0.3545 0.6065
4.250 1.1419 0.00966 0.00351 -0.1565 0.3175 0.6635
4.500 1.1568 0.00995 0.00402 -0.1543 0.2505 0.9971
4.750 1.1710 0.01089 0.00460 -0.1520 0.1852 1.0000
5.000 1.1831 0.01197 0.00526 -0.1494 0.1101 1.0000
5.250 1.1962 0.01294 0.00591 -0.1469 0.0497 1.0000
5.500 1.2171 0.01333 0.00624 -0.1457 0.0390 1.0000
5.750 1.2387 0.01365 0.00653 -0.1446 0.0359 1.0000
6.000 1.2599 0.01395 0.00682 -0.1435 0.0334 1.0000
6.250 1.2798 0.01426 0.00714 -0.1420 0.0313 1.0000
6.500 1.2993 0.01457 0.00745 -0.1405 0.0305 1.0000
6.750 1.3187 0.01487 0.00777 -0.1390 0.0302 1.0000
7.000 1.3379 0.01518 0.00809 -0.1376 0.0295 1.0000
7.250 1.3565 0.01552 0.00846 -0.1360 0.0289 1.0000
7.500 1.3749 0.01588 0.00883 -0.1344 0.0283 1.0000
7.750 1.3929 0.01626 0.00923 -0.1328 0.0275 1.0000
8.000 1.4104 0.01667 0.00966 -0.1312 0.0268 1.0000
8.250 1.4273 0.01713 0.01012 -0.1295 0.0259 1.0000
8.500 1.4437 0.01762 0.01063 -0.1278 0.0250 1.0000
8.750 1.4596 0.01815 0.01118 -0.1260 0.0240 1.0000
9.000 1.4749 0.01873 0.01179 -0.1242 0.0232 1.0000
9.250 1.4905 0.01929 0.01239 -0.1225 0.0227 1.0000
9.500 1.5075 0.01978 0.01290 -0.1210 0.0224 1.0000
9.750 1.5241 0.02029 0.01345 -0.1196 0.0218 1.0000
10.000 1.5399 0.02087 0.01406 -0.1180 0.0213 1.0000
10.250 1.5554 0.02148 0.01468 -0.1165 0.0201 1.0000
10.500 1.5695 0.02218 0.01537 -0.1148 0.0180 1.0000
10.750 1.5792 0.02320 0.01629 -0.1127 0.0099 1.0000
11.000 1.5839 0.02462 0.01771 -0.1100 0.0051 1.0000
11.250 1.5936 0.02572 0.01887 -0.1080 0.0044 1.0000
11.500 1.6025 0.02691 0.02012 -0.1060 0.0038 1.0000
11.750 1.6122 0.02807 0.02134 -0.1042 0.0035 1.0000
12.000 1.6222 0.02925 0.02258 -0.1025 0.0034 1.0000
12.250 1.6316 0.03049 0.02389 -0.1009 0.0033 1.0000
12.500 1.6404 0.03183 0.02529 -0.0993 0.0032 1.0000
12.750 1.6484 0.03327 0.02680 -0.0977 0.0031 1.0000
13.000 1.6557 0.03482 0.02842 -0.0962 0.0030 1.0000
13.250 1.6622 0.03648 0.03017 -0.0947 0.0029 1.0000
13.500 1.6687 0.03821 0.03197 -0.0933 0.0029 1.0000
13.750 1.6740 0.04013 0.03396 -0.0920 0.0027 1.0000
14.000 1.6787 0.04216 0.03607 -0.0908 0.0027 1.0000
14.250 1.6830 0.04429 0.03828 -0.0897 0.0026 1.0000
14.500 1.6863 0.04661 0.04068 -0.0887 0.0025 1.0000
14.750 1.6892 0.04905 0.04321 -0.0879 0.0025 1.0000
15.000 1.6915 0.05163 0.04587 -0.0871 0.0024 1.0000
15.250 1.6920 0.05450 0.04884 -0.0864 0.0023 1.0000
15.500 1.6915 0.05759 0.05203 -0.0859 0.0023 1.0000
15.750 1.6904 0.06085 0.05541 -0.0856 0.0022 1.0000
16.000 1.6871 0.06452 0.05919 -0.0854 0.0022 1.0000
16.250 1.6865 0.06788 0.06265 -0.0854 0.0021 1.0000
16.500 1.6864 0.07126 0.06613 -0.0856 0.0021 1.0000
16.750 1.6848 0.07495 0.06992 -0.0859 0.0021 1.0000
17.000 1.6829 0.07877 0.07384 -0.0864 0.0021 1.0000
17.250 1.6799 0.08283 0.07801 -0.0870 0.0021 1.0000
17.500 1.6768 0.08699 0.08228 -0.0878 0.0021 1.0000
17.750 1.6727 0.09140 0.08680 -0.0889 0.0021 1.0000
18.000 1.6681 0.09600 0.09151 -0.0901 0.0020 1.0000
18.250 1.6629 0.10074 0.09636 -0.0915 0.0020 1.0000
18.500 1.6578 0.10553 0.10126 -0.0930 0.0020 1.0000
18.750 1.6514 0.11063 0.10648 -0.0948 0.0020 1.0000
19.000 1.6450 0.11579 0.11174 -0.0968 0.0019 1.0000
19.250 1.6380 0.12111 0.11718 -0.0989 0.0019 1.0000
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