GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 377 AIRFOIL (goe377-il) Reynolds number: 100,000 Max Cl/Cd: 57.31 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe377-il-100000.txt Download as CSV file: xf-goe377-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 377 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3710 0.09445 0.08967 -0.0244 1.0000 0.0590
-7.500 -0.3767 0.09266 0.08798 -0.0246 1.0000 0.0599
-7.250 -0.3819 0.09121 0.08662 -0.0274 1.0000 0.0610
-7.000 -0.3822 0.08975 0.08519 -0.0314 1.0000 0.0616
-6.750 -0.3797 0.08815 0.08355 -0.0350 1.0000 0.0619
-6.500 -0.3785 0.08272 0.07823 -0.0327 1.0000 0.0627
-6.250 -0.3764 0.07847 0.07404 -0.0279 1.0000 0.0643
-6.000 -0.3737 0.07562 0.07122 -0.0261 1.0000 0.0661
-5.750 -0.3704 0.07293 0.06855 -0.0256 1.0000 0.0684
-5.500 -0.3652 0.07027 0.06588 -0.0259 1.0000 0.0710
-5.250 -0.3455 0.06910 0.06440 -0.0328 1.0000 0.0758
-5.000 -0.3410 0.06454 0.05988 -0.0319 1.0000 0.0771
-4.750 -0.3386 0.06102 0.05647 -0.0287 1.0000 0.0792
-4.500 -0.3300 0.05839 0.05383 -0.0276 1.0000 0.0829
-4.250 -0.3081 0.05565 0.05077 -0.0312 1.0000 0.0914
-4.000 -0.3034 0.05262 0.04789 -0.0285 1.0000 0.0959
-3.750 -0.2830 0.04993 0.04491 -0.0303 1.0000 0.1061
-3.500 -0.2726 0.04724 0.04227 -0.0287 1.0000 0.1116
-3.250 -0.2546 0.04458 0.03940 -0.0291 1.0000 0.1223
-3.000 -0.2364 0.04235 0.03698 -0.0292 1.0000 0.1353
-2.750 -0.2199 0.04012 0.03466 -0.0287 1.0000 0.1499
-2.500 -0.2044 0.03810 0.03260 -0.0278 1.0000 0.1678
-2.250 -0.1880 0.03656 0.03091 -0.0273 1.0000 0.2053
-2.000 -0.1734 0.03451 0.02890 -0.0261 1.0000 0.2354
-1.250 -0.0293 0.02606 0.01776 -0.0330 0.9872 0.1040
-1.000 0.0134 0.02404 0.01542 -0.0356 0.9807 0.1017
-0.750 0.0569 0.02298 0.01394 -0.0383 0.9724 0.1050
-0.500 0.0985 0.02175 0.01255 -0.0408 0.9637 0.1070
-0.250 0.1466 0.02104 0.01178 -0.0446 0.9560 0.1160
0.000 0.1891 0.02018 0.01099 -0.0474 0.9444 0.1247
0.250 0.2337 0.01939 0.01027 -0.0502 0.9323 0.1386
0.500 0.2807 0.01856 0.00966 -0.0535 0.9207 0.1990
0.750 0.3693 0.01629 0.00897 -0.0653 0.9179 1.0000
1.000 0.4162 0.01614 0.00867 -0.0687 0.9057 1.0000
1.250 0.4649 0.01587 0.00831 -0.0723 0.8941 1.0000
1.500 0.5096 0.01557 0.00797 -0.0750 0.8820 1.0000
1.750 0.5499 0.01527 0.00765 -0.0767 0.8683 1.0000
2.000 0.5852 0.01501 0.00738 -0.0774 0.8527 1.0000
2.250 0.6183 0.01476 0.00712 -0.0775 0.8359 1.0000
2.500 0.6506 0.01449 0.00685 -0.0774 0.8184 1.0000
2.750 0.6787 0.01432 0.00671 -0.0765 0.7981 1.0000
3.000 0.7067 0.01416 0.00653 -0.0756 0.7764 1.0000
3.250 0.7325 0.01409 0.00644 -0.0743 0.7520 1.0000
3.500 0.7583 0.01407 0.00638 -0.0731 0.7257 1.0000
3.750 0.7832 0.01414 0.00643 -0.0717 0.6968 1.0000
4.000 0.8072 0.01429 0.00651 -0.0702 0.6658 1.0000
4.250 0.8307 0.01454 0.00663 -0.0687 0.6332 1.0000
4.500 0.8522 0.01487 0.00686 -0.0669 0.5970 1.0000
4.750 0.8739 0.01528 0.00715 -0.0653 0.5624 1.0000
5.000 0.8950 0.01576 0.00754 -0.0636 0.5289 1.0000
5.250 0.9167 0.01629 0.00800 -0.0622 0.4998 1.0000
5.500 0.9387 0.01685 0.00852 -0.0609 0.4740 1.0000
5.750 0.9606 0.01740 0.00901 -0.0596 0.4498 1.0000
6.000 0.9811 0.01788 0.00954 -0.0581 0.4241 1.0000
6.250 0.9995 0.01828 0.00990 -0.0562 0.3952 1.0000
6.500 1.0169 0.01868 0.01029 -0.0542 0.3645 1.0000
6.750 1.0325 0.01906 0.01069 -0.0520 0.3294 1.0000
7.000 1.0477 0.01951 0.01115 -0.0498 0.2920 1.0000
7.250 1.0594 0.02010 0.01171 -0.0469 0.2190 1.0000
7.500 1.0562 0.02322 0.01354 -0.0424 0.0768 1.0000
7.750 1.0654 0.02508 0.01534 -0.0394 0.0621 1.0000
8.000 1.0720 0.02708 0.01734 -0.0361 0.0562 1.0000
8.250 1.0849 0.02872 0.01913 -0.0336 0.0526 1.0000
8.500 1.0998 0.03059 0.02103 -0.0315 0.0490 1.0000
8.750 1.1203 0.03378 0.02409 -0.0307 0.0447 1.0000
9.000 1.1426 0.03585 0.02643 -0.0295 0.0430 1.0000
9.250 1.1656 0.03867 0.02960 -0.0285 0.0422 1.0000
9.500 1.1844 0.04180 0.03309 -0.0271 0.0421 1.0000
9.750 1.1974 0.04531 0.03702 -0.0251 0.0423 1.0000
10.000 1.2053 0.04902 0.04115 -0.0227 0.0428 1.0000
10.250 1.2076 0.05261 0.04515 -0.0200 0.0430 1.0000
10.500 1.2057 0.05642 0.04933 -0.0172 0.0434 1.0000
10.750 1.1982 0.05971 0.05298 -0.0140 0.0432 1.0000
11.000 1.1887 0.06370 0.05723 -0.0112 0.0438 1.0000
11.250 1.1717 0.06664 0.06042 -0.0077 0.0437 1.0000
11.500 1.1556 0.07067 0.06465 -0.0056 0.0441 1.0000
11.750 1.1358 0.07439 0.06859 -0.0042 0.0441 1.0000
12.000 1.0396 0.07332 0.06793 0.0011 0.0456 1.0000
12.250 1.0060 0.07757 0.07248 0.0002 0.0468 1.0000
12.500 0.9465 0.08678 0.08204 -0.0053 0.0485 1.0000
12.750 0.9097 0.09551 0.09092 -0.0107 0.0489 1.0000
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Polar data table (+)
Polar graphs
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