GOE 500 AIRFOIL (goe500-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 500 AIRFOIL (goe500-il) Reynolds number: 200,000 Max Cl/Cd: 92.04 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe500-il-200000.txt Download as CSV file: xf-goe500-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1686 0.09534 0.09209 -0.0573 0.9754 0.0606
-8.750 -0.1556 0.09144 0.08817 -0.0604 0.9729 0.0633
-8.500 -0.2733 0.10178 0.09841 -0.0492 0.9852 0.0588
-8.250 -0.2515 0.09847 0.09508 -0.0524 0.9832 0.0608
-8.000 -0.2409 0.09546 0.09208 -0.0550 0.9773 0.0635
-7.750 -0.2417 0.09234 0.08898 -0.0665 0.9682 0.0673
-7.500 -0.2346 0.08687 0.08354 -0.0728 0.9598 0.0681
-7.250 -0.2094 0.08456 0.08119 -0.0682 0.9598 0.0701
-7.000 -0.1845 0.08153 0.07813 -0.0716 0.9570 0.0735
-6.750 -0.1619 0.07426 0.07079 -0.0974 0.9426 0.0795
-6.500 -0.1469 0.07025 0.06681 -0.0942 0.9413 0.0808
-6.250 -0.1392 0.06870 0.06527 -0.0909 0.9334 0.0819
-6.000 -0.1145 0.06648 0.06303 -0.0922 0.9297 0.0854
-5.750 -0.0702 0.04185 0.03775 -0.1311 0.9188 0.0663
-5.500 -0.0304 0.03219 0.02734 -0.1426 0.9147 0.0636
-5.250 0.0132 0.02664 0.02093 -0.1493 0.9128 0.0646
-5.000 0.0560 0.02387 0.01753 -0.1534 0.9113 0.0665
-4.750 0.0976 0.02196 0.01528 -0.1567 0.9101 0.0696
-4.500 0.1156 0.02140 0.01464 -0.1550 0.9012 0.0716
-4.250 0.1544 0.02042 0.01347 -0.1571 0.8986 0.0752
-4.000 0.1947 0.01955 0.01232 -0.1593 0.8963 0.0797
-3.750 0.2360 0.01853 0.01133 -0.1617 0.8944 0.0863
-3.500 0.2596 0.01812 0.01075 -0.1606 0.8850 0.0923
-3.250 0.2971 0.01722 0.00986 -0.1621 0.8815 0.1040
-3.000 0.3346 0.01649 0.00908 -0.1637 0.8791 0.1210
-2.750 0.3567 0.01614 0.00876 -0.1626 0.8706 0.1353
-2.500 0.3896 0.01566 0.00827 -0.1634 0.8666 0.1511
-2.250 0.4245 0.01519 0.00781 -0.1645 0.8638 0.1661
-2.000 0.4474 0.01505 0.00771 -0.1635 0.8554 0.1785
-1.750 0.4793 0.01468 0.00737 -0.1640 0.8510 0.1940
-1.500 0.5135 0.01426 0.00698 -0.1648 0.8479 0.2120
-1.250 0.5362 0.01415 0.00693 -0.1637 0.8388 0.2308
-1.000 0.5683 0.01371 0.00665 -0.1642 0.8346 0.2689
-0.750 0.5948 0.01348 0.00658 -0.1638 0.8275 0.3252
-0.500 0.6239 0.01320 0.00642 -0.1638 0.8213 0.3744
-0.250 0.6545 0.01292 0.00623 -0.1639 0.8161 0.4164
0.000 0.6797 0.01281 0.00622 -0.1632 0.8076 0.4559
0.250 0.7112 0.01252 0.00601 -0.1635 0.8028 0.5012
0.500 0.7353 0.01243 0.00608 -0.1626 0.7936 0.5469
0.750 0.7656 0.01211 0.00587 -0.1627 0.7879 0.6066
1.000 0.7882 0.01188 0.00589 -0.1613 0.7782 0.6859
1.250 0.8209 0.01122 0.00559 -0.1616 0.7717 1.0000
1.500 0.8473 0.01129 0.00559 -0.1612 0.7618 1.0000
1.750 0.8757 0.01134 0.00555 -0.1610 0.7533 1.0000
2.000 0.9044 0.01137 0.00550 -0.1609 0.7444 1.0000
2.250 0.9309 0.01149 0.00556 -0.1605 0.7340 1.0000
2.500 0.9594 0.01156 0.00556 -0.1603 0.7246 1.0000
2.750 0.9864 0.01167 0.00561 -0.1600 0.7139 1.0000
3.000 1.0124 0.01184 0.00575 -0.1595 0.7028 1.0000
3.250 1.0396 0.01199 0.00585 -0.1591 0.6922 1.0000
3.500 1.0671 0.01214 0.00594 -0.1589 0.6815 1.0000
3.750 1.0919 0.01234 0.00614 -0.1582 0.6691 1.0000
4.000 1.1174 0.01253 0.00632 -0.1575 0.6568 1.0000
4.250 1.1427 0.01272 0.00648 -0.1569 0.6439 1.0000
4.500 1.1676 0.01290 0.00663 -0.1561 0.6302 1.0000
4.750 1.1919 0.01308 0.00677 -0.1552 0.6156 1.0000
5.000 1.2158 0.01328 0.00695 -0.1543 0.6010 1.0000
5.250 1.2392 0.01349 0.00714 -0.1533 0.5862 1.0000
5.500 1.2616 0.01371 0.00735 -0.1521 0.5702 1.0000
5.750 1.2831 0.01394 0.00757 -0.1507 0.5527 1.0000
6.000 1.3041 0.01420 0.00783 -0.1493 0.5347 1.0000
6.250 1.3244 0.01448 0.00808 -0.1478 0.5159 1.0000
6.500 1.3442 0.01483 0.00837 -0.1462 0.4972 1.0000
6.750 1.3626 0.01519 0.00873 -0.1443 0.4763 1.0000
7.000 1.3802 0.01560 0.00913 -0.1424 0.4554 1.0000
7.250 1.3960 0.01608 0.00957 -0.1402 0.4319 1.0000
7.500 1.4083 0.01665 0.01006 -0.1373 0.4022 1.0000
7.750 1.4151 0.01736 0.01065 -0.1336 0.3584 1.0000
8.000 1.4072 0.01860 0.01147 -0.1276 0.2802 1.0000
8.250 1.3896 0.02083 0.01306 -0.1208 0.1922 1.0000
8.500 1.3731 0.02348 0.01509 -0.1149 0.1104 1.0000
8.750 1.3698 0.02547 0.01686 -0.1110 0.0822 1.0000
9.000 1.3720 0.02713 0.01847 -0.1078 0.0721 1.0000
9.250 1.3767 0.02867 0.02005 -0.1051 0.0657 1.0000
9.500 1.3768 0.03060 0.02201 -0.1021 0.0614 1.0000
9.750 1.3826 0.03219 0.02370 -0.0999 0.0579 1.0000
10.000 1.3858 0.03404 0.02560 -0.0975 0.0548 1.0000
10.250 1.3838 0.03647 0.02803 -0.0949 0.0521 1.0000
10.500 1.3897 0.03833 0.03001 -0.0930 0.0497 1.0000
10.750 1.3965 0.04016 0.03193 -0.0912 0.0475 1.0000
11.000 1.4033 0.04207 0.03389 -0.0896 0.0454 1.0000
11.250 1.4105 0.04414 0.03594 -0.0880 0.0433 1.0000
11.500 1.4235 0.04611 0.03794 -0.0865 0.0411 1.0000
11.750 1.4360 0.04774 0.03970 -0.0852 0.0394 1.0000
12.000 1.4508 0.04941 0.04148 -0.0840 0.0378 1.0000
12.250 1.4658 0.05114 0.04327 -0.0830 0.0363 1.0000
12.500 1.5063 0.05327 0.04531 -0.0832 0.0337 1.0000
12.750 1.5084 0.05530 0.04759 -0.0815 0.0329 1.0000
13.000 1.5171 0.05757 0.05010 -0.0802 0.0320 1.0000
13.250 1.5270 0.06012 0.05289 -0.0790 0.0312 1.0000
13.500 1.5348 0.06293 0.05593 -0.0778 0.0305 1.0000
13.750 1.5398 0.06593 0.05916 -0.0767 0.0299 1.0000
14.000 1.5431 0.06892 0.06233 -0.0757 0.0293 1.0000
14.250 1.5489 0.07169 0.06519 -0.0750 0.0285 1.0000
14.500 1.5526 0.07500 0.06861 -0.0744 0.0277 1.0000
15.000 1.5394 0.08572 0.07984 -0.0734 0.0269 1.0000
15.250 1.5232 0.09048 0.08486 -0.0732 0.0269 1.0000
15.500 1.5070 0.09570 0.09034 -0.0735 0.0269 1.0000
15.750 1.4901 0.10130 0.09620 -0.0744 0.0269 1.0000
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