GOE 602 AIRFOIL (goe602-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 602 AIRFOIL (goe602-il) Reynolds number: 100,000 Max Cl/Cd: 57.55 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe602-il-100000-n5.txt Download as CSV file: xf-goe602-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 602 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3834 0.09193 0.08719 -0.0400 1.0000 0.0285
-8.500 -0.3912 0.08887 0.08422 -0.0398 1.0000 0.0286
-8.250 -0.4014 0.08606 0.08149 -0.0390 1.0000 0.0285
-8.000 -0.4174 0.08338 0.07893 -0.0378 1.0000 0.0287
-7.750 -0.4321 0.08102 0.07665 -0.0362 1.0000 0.0285
-7.500 -0.4434 0.07768 0.07339 -0.0363 1.0000 0.0283
-7.250 -0.4525 0.07398 0.06973 -0.0371 1.0000 0.0282
-7.000 -0.4596 0.06973 0.06549 -0.0383 1.0000 0.0280
-6.750 -0.4432 0.06132 0.05689 -0.0473 0.9944 0.0281
-6.500 -0.4239 0.05351 0.04876 -0.0546 0.9879 0.0281
-6.250 -0.4039 0.04612 0.04086 -0.0599 0.9815 0.0283
-6.000 -0.3782 0.03966 0.03362 -0.0641 0.9764 0.0292
-5.750 -0.3564 0.03588 0.02939 -0.0658 0.9703 0.0315
-5.500 -0.3264 0.03342 0.02661 -0.0680 0.9662 0.0337
-5.250 -0.3002 0.03048 0.02313 -0.0687 0.9605 0.0356
-5.000 -0.2691 0.02823 0.02026 -0.0699 0.9558 0.0395
-4.750 -0.2350 0.02584 0.01733 -0.0715 0.9526 0.0425
-4.500 -0.2096 0.02465 0.01604 -0.0715 0.9457 0.0463
-4.250 -0.1761 0.02345 0.01452 -0.0727 0.9413 0.0507
-4.000 -0.1412 0.02231 0.01307 -0.0740 0.9374 0.0537
-3.750 -0.1146 0.02133 0.01211 -0.0741 0.9303 0.0584
-3.500 -0.0796 0.02044 0.01113 -0.0755 0.9261 0.0619
-3.250 -0.0501 0.01974 0.01029 -0.0757 0.9196 0.0652
-3.000 -0.0179 0.01905 0.00953 -0.0766 0.9137 0.0695
-2.750 0.0202 0.01844 0.00886 -0.0786 0.9100 0.0789
-2.500 0.0459 0.01798 0.00839 -0.0782 0.9010 0.0940
-2.250 0.0827 0.01719 0.00777 -0.0800 0.8966 0.1363
-2.000 0.1090 0.01641 0.00749 -0.0800 0.8882 0.2562
-1.750 0.1439 0.01576 0.00719 -0.0815 0.8828 0.3808
-1.500 0.1678 0.01503 0.00715 -0.0806 0.8742 0.5576
-1.250 0.1969 0.01418 0.00712 -0.0793 0.8689 0.8054
-1.000 0.2742 0.01382 0.00674 -0.0889 0.8677 1.0000
-0.750 0.2997 0.01380 0.00654 -0.0883 0.8568 1.0000
-0.500 0.3284 0.01375 0.00633 -0.0884 0.8471 1.0000
-0.250 0.3617 0.01363 0.00606 -0.0893 0.8391 1.0000
0.250 0.4145 0.01361 0.00581 -0.0884 0.8157 1.0000
0.500 0.4431 0.01357 0.00568 -0.0884 0.8044 1.0000
0.750 0.4728 0.01353 0.00554 -0.0885 0.7931 1.0000
1.000 0.5032 0.01348 0.00540 -0.0888 0.7816 1.0000
1.250 0.5307 0.01349 0.00535 -0.0885 0.7681 1.0000
1.500 0.5587 0.01351 0.00531 -0.0884 0.7543 1.0000
1.750 0.5867 0.01354 0.00527 -0.0882 0.7401 1.0000
2.000 0.6147 0.01359 0.00526 -0.0880 0.7253 1.0000
2.250 0.6424 0.01367 0.00528 -0.0877 0.7100 1.0000
2.500 0.6697 0.01376 0.00532 -0.0874 0.6943 1.0000
2.750 0.6954 0.01390 0.00541 -0.0868 0.6773 1.0000
3.000 0.7210 0.01406 0.00554 -0.0862 0.6600 1.0000
3.250 0.7464 0.01423 0.00568 -0.0856 0.6428 1.0000
3.500 0.7715 0.01442 0.00582 -0.0849 0.6247 1.0000
3.750 0.7963 0.01463 0.00600 -0.0842 0.6062 1.0000
4.000 0.8199 0.01487 0.00623 -0.0832 0.5870 1.0000
4.250 0.8435 0.01512 0.00646 -0.0823 0.5680 1.0000
4.500 0.8672 0.01539 0.00673 -0.0814 0.5501 1.0000
4.750 0.8904 0.01569 0.00703 -0.0805 0.5320 1.0000
5.000 0.9133 0.01599 0.00736 -0.0795 0.5145 1.0000
5.250 0.9358 0.01632 0.00771 -0.0785 0.4965 1.0000
5.500 0.9582 0.01666 0.00811 -0.0774 0.4789 1.0000
5.750 0.9800 0.01703 0.00849 -0.0763 0.4606 1.0000
6.000 1.0006 0.01741 0.00893 -0.0749 0.4394 1.0000
6.250 1.0180 0.01785 0.00931 -0.0730 0.4082 1.0000
6.500 1.0319 0.01841 0.00970 -0.0705 0.3639 1.0000
6.750 1.0447 0.01911 0.01021 -0.0680 0.3137 1.0000
7.000 1.0581 0.01989 0.01080 -0.0658 0.2662 1.0000
7.250 1.0691 0.02092 0.01154 -0.0633 0.2117 1.0000
7.500 1.0759 0.02237 0.01252 -0.0604 0.1364 1.0000
7.750 1.0803 0.02411 0.01379 -0.0572 0.0798 1.0000
8.000 1.0839 0.02579 0.01511 -0.0538 0.0379 1.0000
8.250 1.0926 0.02700 0.01641 -0.0509 0.0331 1.0000
8.500 1.1005 0.02827 0.01782 -0.0481 0.0302 1.0000
8.750 1.1036 0.02987 0.01956 -0.0449 0.0274 1.0000
9.000 1.1101 0.03122 0.02113 -0.0422 0.0258 1.0000
9.250 1.1155 0.03266 0.02277 -0.0395 0.0247 1.0000
9.500 1.1195 0.03424 0.02453 -0.0370 0.0239 1.0000
9.750 1.1224 0.03598 0.02644 -0.0345 0.0231 1.0000
10.000 1.1251 0.03783 0.02843 -0.0322 0.0222 1.0000
10.250 1.1280 0.03979 0.03052 -0.0302 0.0211 1.0000
10.500 1.1309 0.04186 0.03270 -0.0284 0.0200 1.0000
10.750 1.1340 0.04410 0.03503 -0.0267 0.0190 1.0000
11.000 1.1398 0.04645 0.03745 -0.0252 0.0184 1.0000
11.250 1.1513 0.04892 0.03999 -0.0239 0.0178 1.0000
11.500 1.1717 0.05195 0.04315 -0.0230 0.0173 1.0000
11.750 1.1819 0.05454 0.04592 -0.0219 0.0170 1.0000
12.000 1.1864 0.05714 0.04885 -0.0207 0.0168 1.0000
12.250 1.1873 0.05991 0.05188 -0.0196 0.0166 1.0000
12.500 1.1850 0.06289 0.05514 -0.0187 0.0162 1.0000
12.750 1.1804 0.06618 0.05870 -0.0181 0.0159 1.0000
13.000 1.1742 0.06982 0.06260 -0.0179 0.0156 1.0000
13.250 1.1657 0.07382 0.06686 -0.0181 0.0153 1.0000
13.500 1.1558 0.07819 0.07148 -0.0188 0.0152 1.0000
13.750 1.1437 0.08304 0.07658 -0.0200 0.0151 1.0000
14.000 1.1306 0.08830 0.08208 -0.0218 0.0151 1.0000
14.250 1.1160 0.09406 0.08806 -0.0243 0.0150 1.0000
14.500 1.1001 0.10041 0.09464 -0.0274 0.0150 1.0000
14.750 1.0836 0.10731 0.10174 -0.0311 0.0151 1.0000
15.000 1.0671 0.11471 0.10933 -0.0355 0.0151 1.0000
15.250 1.0502 0.12271 0.11751 -0.0404 0.0153 1.0000
15.500 1.0328 0.13142 0.12636 -0.0460 0.0155 1.0000
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Polar data table (+)
Polar graphs
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