GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 397 AIRFOIL (goe397-il) Reynolds number: 100,000 Max Cl/Cd: 60.98 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe397-il-100000-n5.txt Download as CSV file: xf-goe397-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 397 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3737 0.09415 0.08927 -0.0204 1.0000 0.0314
-7.500 -0.3712 0.09150 0.08668 -0.0210 1.0000 0.0318
-7.250 -0.3692 0.08887 0.08412 -0.0217 1.0000 0.0325
-7.000 -0.3644 0.08598 0.08129 -0.0232 1.0000 0.0334
-6.750 -0.3585 0.08306 0.07842 -0.0250 1.0000 0.0343
-6.500 -0.3511 0.08011 0.07551 -0.0274 1.0000 0.0356
-6.250 -0.3369 0.07767 0.07309 -0.0337 1.0000 0.0379
-6.000 -0.3218 0.07471 0.07011 -0.0380 1.0000 0.0384
-5.750 -0.3063 0.07155 0.06689 -0.0413 1.0000 0.0387
-5.250 -0.3016 0.06389 0.05939 -0.0383 1.0000 0.0409
-5.000 -0.2971 0.06153 0.05706 -0.0367 1.0000 0.0431
-4.750 -0.2614 0.05713 0.05252 -0.0433 0.9923 0.0465
-4.250 -0.1840 0.04809 0.04307 -0.0564 0.9765 0.0570
-4.000 -0.1405 0.04293 0.03752 -0.0623 0.9681 0.0496
-3.750 -0.1047 0.03819 0.03248 -0.0662 0.9598 0.0446
-3.500 -0.0644 0.03451 0.02838 -0.0701 0.9535 0.0486
-3.250 -0.0300 0.03099 0.02443 -0.0723 0.9445 0.0484
-3.000 0.0066 0.02782 0.02074 -0.0745 0.9377 0.0489
-2.750 0.0420 0.02592 0.01813 -0.0756 0.9287 0.0522
-2.500 0.0741 0.02359 0.01543 -0.0767 0.9202 0.0518
-2.250 0.1079 0.02179 0.01321 -0.0778 0.9126 0.0519
-2.000 0.1387 0.02045 0.01152 -0.0783 0.9032 0.0523
-1.750 0.1710 0.01893 0.00972 -0.0792 0.8957 0.0534
-1.500 0.2010 0.01816 0.00889 -0.0798 0.8862 0.0581
-1.250 0.2313 0.01746 0.00802 -0.0801 0.8770 0.0607
-1.000 0.2627 0.01667 0.00707 -0.0805 0.8693 0.0605
-0.750 0.2909 0.01608 0.00639 -0.0804 0.8594 0.0604
-0.500 0.3192 0.01557 0.00584 -0.0803 0.8502 0.0606
0.000 0.3753 0.01486 0.00497 -0.0798 0.8303 0.0619
0.250 0.4023 0.01463 0.00464 -0.0793 0.8173 0.0631
0.500 0.4294 0.01447 0.00437 -0.0787 0.8042 0.0652
0.750 0.4566 0.01433 0.00420 -0.0783 0.7926 0.0698
1.000 0.4840 0.01421 0.00410 -0.0780 0.7826 0.0848
1.250 0.5273 0.01215 0.00409 -0.0815 0.7735 1.0000
1.500 0.5530 0.01229 0.00413 -0.0809 0.7630 1.0000
1.750 0.5790 0.01243 0.00418 -0.0803 0.7533 1.0000
2.000 0.6049 0.01257 0.00426 -0.0797 0.7437 1.0000
2.250 0.6304 0.01273 0.00441 -0.0791 0.7330 1.0000
2.500 0.6560 0.01289 0.00459 -0.0785 0.7230 1.0000
2.750 0.6819 0.01304 0.00474 -0.0779 0.7133 1.0000
3.000 0.7073 0.01320 0.00495 -0.0773 0.7024 1.0000
3.250 0.7327 0.01338 0.00522 -0.0767 0.6913 1.0000
3.500 0.7581 0.01355 0.00545 -0.0760 0.6795 1.0000
3.750 0.7829 0.01370 0.00566 -0.0750 0.6638 1.0000
4.000 0.8070 0.01382 0.00577 -0.0738 0.6421 1.0000
4.250 0.8297 0.01395 0.00594 -0.0723 0.6110 1.0000
4.500 0.8517 0.01412 0.00609 -0.0707 0.5729 1.0000
4.750 0.8739 0.01433 0.00634 -0.0693 0.5303 1.0000
5.000 0.8943 0.01468 0.00652 -0.0675 0.4625 1.0000
5.250 0.9116 0.01547 0.00693 -0.0654 0.3806 1.0000
5.500 0.9262 0.01675 0.00767 -0.0633 0.2567 1.0000
5.750 0.9350 0.01903 0.00898 -0.0610 0.1154 1.0000
6.000 0.9518 0.02038 0.01011 -0.0595 0.0801 1.0000
6.250 0.9695 0.02157 0.01130 -0.0581 0.0613 1.0000
6.500 0.9861 0.02289 0.01270 -0.0564 0.0465 1.0000
6.750 1.0016 0.02429 0.01422 -0.0546 0.0372 1.0000
7.000 1.0181 0.02557 0.01555 -0.0529 0.0312 1.0000
7.250 1.0338 0.02728 0.01740 -0.0510 0.0281 1.0000
7.500 1.0523 0.02881 0.01908 -0.0495 0.0245 1.0000
7.750 1.0700 0.03039 0.02072 -0.0482 0.0218 1.0000
8.000 1.0892 0.03323 0.02369 -0.0470 0.0204 1.0000
8.250 1.1105 0.03595 0.02675 -0.0457 0.0197 1.0000
8.500 1.1292 0.03886 0.03018 -0.0443 0.0185 1.0000
8.750 1.1439 0.04189 0.03368 -0.0425 0.0171 1.0000
9.000 1.1545 0.04535 0.03760 -0.0405 0.0163 1.0000
9.250 1.1601 0.04920 0.04193 -0.0382 0.0161 1.0000
9.500 1.1607 0.05320 0.04638 -0.0357 0.0159 1.0000
9.750 1.1565 0.05721 0.05078 -0.0332 0.0159 1.0000
10.000 1.1474 0.06109 0.05499 -0.0306 0.0159 1.0000
10.250 1.1328 0.06470 0.05887 -0.0278 0.0159 1.0000
10.500 1.1160 0.06854 0.06294 -0.0260 0.0160 1.0000
10.750 1.0978 0.07287 0.06747 -0.0256 0.0160 1.0000
11.000 1.0788 0.07778 0.07257 -0.0265 0.0161 1.0000
11.250 1.0591 0.08344 0.07839 -0.0287 0.0163 1.0000
11.500 1.0389 0.09005 0.08515 -0.0323 0.0164 1.0000
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Polar data table (+)
Polar graphs
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