GOE 415 AIRFOIL (goe415-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 415 AIRFOIL (goe415-il) Reynolds number: 50,000 Max Cl/Cd: 37.23 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe415-il-50000-n5.txt Download as CSV file: xf-goe415-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 415 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4295 0.13307 0.12629 0.0002 1.0000 0.0700
-10.000 -0.4317 0.13156 0.12486 -0.0031 1.0000 0.0716
-9.750 -0.4340 0.12993 0.12331 -0.0065 1.0000 0.0721
-9.500 -0.4124 0.12264 0.11602 -0.0030 1.0000 0.0770
-9.250 -0.4068 0.11954 0.11296 -0.0041 1.0000 0.0814
-9.000 -0.4084 0.11761 0.11112 -0.0073 1.0000 0.0851
-8.750 -0.4137 0.11622 0.10985 -0.0115 1.0000 0.0861
-8.500 -0.3938 0.10995 0.10357 -0.0082 1.0000 0.0909
-8.250 -0.3888 0.10696 0.10064 -0.0094 1.0000 0.0958
-8.000 -0.3959 0.10562 0.09944 -0.0138 1.0000 0.0996
-7.750 -0.3882 0.10131 0.09521 -0.0138 1.0000 0.1022
-7.500 -0.3770 0.09762 0.09155 -0.0129 1.0000 0.1080
-7.250 -0.3826 0.09607 0.09013 -0.0197 1.0000 0.1140
-7.000 -0.3711 0.09151 0.08559 -0.0170 1.0000 0.1183
-6.750 -0.3663 0.08884 0.08299 -0.0206 1.0000 0.1274
-6.250 -0.3544 0.08271 0.07698 -0.0290 1.0000 0.1439
-6.000 -0.3431 0.07864 0.07299 -0.0233 1.0000 0.1494
-5.500 -0.3287 0.07255 0.06701 -0.0283 1.0000 0.1742
-5.000 -0.2766 0.05916 0.05315 -0.0417 1.0000 0.0697
-4.750 -0.2570 0.05446 0.04825 -0.0436 1.0000 0.0554
-4.500 -0.2406 0.05078 0.04445 -0.0445 1.0000 0.0525
-4.250 -0.2208 0.04698 0.04040 -0.0459 1.0000 0.0502
-4.000 -0.1988 0.04330 0.03635 -0.0472 1.0000 0.0483
-3.750 -0.1736 0.04000 0.03246 -0.0481 1.0000 0.0460
-3.500 -0.1496 0.03796 0.02986 -0.0479 1.0000 0.0445
-3.250 -0.1278 0.03511 0.02672 -0.0479 1.0000 0.0438
-3.000 -0.1045 0.03275 0.02401 -0.0478 1.0000 0.0433
-2.750 -0.0574 0.03000 0.02065 -0.0515 0.9891 0.0436
-2.500 -0.0110 0.02740 0.01761 -0.0553 0.9773 0.0475
-2.250 0.0338 0.02545 0.01534 -0.0581 0.9632 0.0507
-2.000 0.0788 0.02384 0.01337 -0.0607 0.9484 0.0543
-1.750 0.1244 0.02242 0.01170 -0.0635 0.9328 0.0642
-1.500 0.1687 0.02134 0.01031 -0.0659 0.9150 0.0729
-1.250 0.2098 0.02018 0.00919 -0.0681 0.8947 0.1054
-1.000 0.2467 0.01671 0.00860 -0.0687 0.8741 1.0000
-0.750 0.2803 0.01675 0.00803 -0.0689 0.8465 1.0000
-0.500 0.3113 0.01679 0.00759 -0.0688 0.8175 1.0000
-0.250 0.3411 0.01684 0.00723 -0.0685 0.7887 1.0000
0.000 0.3699 0.01691 0.00692 -0.0679 0.7612 1.0000
0.250 0.3978 0.01703 0.00666 -0.0672 0.7351 1.0000
0.500 0.4248 0.01720 0.00648 -0.0664 0.7105 1.0000
0.750 0.4511 0.01743 0.00640 -0.0656 0.6869 1.0000
1.000 0.4770 0.01771 0.00639 -0.0648 0.6639 1.0000
1.250 0.5028 0.01800 0.00642 -0.0641 0.6430 1.0000
1.500 0.5284 0.01833 0.00654 -0.0634 0.6226 1.0000
1.750 0.5541 0.01866 0.00668 -0.0628 0.6035 1.0000
2.000 0.5798 0.01901 0.00685 -0.0622 0.5859 1.0000
2.250 0.6055 0.01938 0.00705 -0.0616 0.5695 1.0000
2.500 0.6316 0.01978 0.00734 -0.0612 0.5534 1.0000
2.750 0.6578 0.02020 0.00766 -0.0608 0.5378 1.0000
3.000 0.6839 0.02063 0.00802 -0.0605 0.5231 1.0000
3.250 0.7100 0.02108 0.00845 -0.0601 0.5094 1.0000
3.500 0.7361 0.02155 0.00887 -0.0598 0.4964 1.0000
3.750 0.7618 0.02204 0.00937 -0.0594 0.4833 1.0000
4.000 0.7874 0.02255 0.00998 -0.0591 0.4708 1.0000
4.250 0.8129 0.02309 0.01057 -0.0588 0.4589 1.0000
4.500 0.8384 0.02363 0.01117 -0.0584 0.4478 1.0000
4.750 0.8641 0.02416 0.01173 -0.0580 0.4379 1.0000
5.000 0.8891 0.02477 0.01253 -0.0577 0.4270 1.0000
5.250 0.9139 0.02541 0.01332 -0.0573 0.4166 1.0000
5.500 0.9390 0.02601 0.01402 -0.0569 0.4072 1.0000
5.750 0.9636 0.02663 0.01485 -0.0564 0.3972 1.0000
6.000 0.9871 0.02725 0.01565 -0.0558 0.3852 1.0000
6.250 1.0103 0.02780 0.01637 -0.0551 0.3726 1.0000
6.500 1.0333 0.02834 0.01709 -0.0544 0.3601 1.0000
6.750 1.0564 0.02892 0.01785 -0.0537 0.3486 1.0000
7.000 1.0800 0.02955 0.01872 -0.0530 0.3386 1.0000
7.250 1.1020 0.03037 0.01989 -0.0522 0.3276 1.0000
7.500 1.1205 0.03046 0.02009 -0.0507 0.3060 1.0000
7.750 1.1345 0.03047 0.02018 -0.0489 0.2743 1.0000
8.000 1.1513 0.03095 0.02080 -0.0475 0.2520 1.0000
8.250 1.1677 0.03167 0.02177 -0.0463 0.2262 1.0000
8.500 1.1821 0.03258 0.02281 -0.0449 0.1892 1.0000
8.750 1.1933 0.03399 0.02420 -0.0434 0.1381 1.0000
9.250 1.1831 0.04069 0.02993 -0.0397 0.0397 1.0000
9.500 1.1784 0.04368 0.03302 -0.0379 0.0352 1.0000
9.750 1.1705 0.04700 0.03650 -0.0366 0.0329 1.0000
10.000 1.1609 0.05086 0.04051 -0.0363 0.0315 1.0000
10.250 1.1527 0.05499 0.04490 -0.0370 0.0305 1.0000
10.500 1.1438 0.05967 0.04982 -0.0384 0.0299 1.0000
10.750 1.1343 0.06477 0.05514 -0.0404 0.0295 1.0000
11.000 1.1246 0.07005 0.06063 -0.0424 0.0291 1.0000
11.250 1.1150 0.07535 0.06612 -0.0444 0.0288 1.0000
11.500 1.1056 0.08060 0.07154 -0.0462 0.0284 1.0000
11.750 1.0970 0.08572 0.07681 -0.0479 0.0281 1.0000
12.000 1.0893 0.09068 0.08190 -0.0494 0.0278 1.0000
12.250 1.0827 0.09542 0.08677 -0.0508 0.0274 1.0000
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Polar data table (+)
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