GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 613 AIRFOIL (goe613-il) Reynolds number: 100,000 Max Cl/Cd: 52.84 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe613-il-100000-n5.txt Download as CSV file: xf-goe613-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 613 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3529 0.09821 0.09369 -0.0329 1.0000 0.0560
-8.000 -0.3737 0.09708 0.09267 -0.0315 1.0000 0.0564
-7.750 -0.3931 0.09566 0.09135 -0.0298 1.0000 0.0566
-7.500 -0.3869 0.09079 0.08645 -0.0393 0.9942 0.0570
-7.250 -0.3700 0.08515 0.08068 -0.0475 0.9871 0.0572
-7.000 -0.3582 0.08003 0.07565 -0.0465 0.9843 0.0582
-6.750 -0.3433 0.07728 0.07293 -0.0448 0.9804 0.0602
-6.500 -0.3229 0.07372 0.06930 -0.0486 0.9755 0.0646
-6.000 -0.2880 0.06348 0.05874 -0.0612 0.9594 0.0723
-5.750 -0.2644 0.05702 0.05201 -0.0650 0.9533 0.0544
-5.500 -0.2429 0.05253 0.04724 -0.0680 0.9461 0.0549
-5.250 -0.2181 0.04824 0.04267 -0.0707 0.9396 0.0544
-5.000 -0.1930 0.04429 0.03842 -0.0727 0.9329 0.0528
-4.500 -0.1314 0.03722 0.03048 -0.0769 0.9213 0.0541
-4.250 -0.1104 0.03475 0.02763 -0.0763 0.9121 0.0541
-4.000 -0.0781 0.03211 0.02457 -0.0777 0.9082 0.0538
-3.750 -0.0530 0.03018 0.02228 -0.0775 0.9016 0.0537
-3.500 -0.0237 0.02839 0.02012 -0.0779 0.8960 0.0539
-3.250 0.0121 0.02692 0.01820 -0.0793 0.8926 0.0558
-3.000 0.0371 0.02597 0.01693 -0.0785 0.8850 0.0569
-2.750 0.0703 0.02469 0.01537 -0.0794 0.8801 0.0570
-2.250 0.1308 0.02242 0.01278 -0.0800 0.8676 0.0579
-2.000 0.1668 0.02128 0.01156 -0.0813 0.8630 0.0588
-1.750 0.1927 0.02052 0.01077 -0.0807 0.8532 0.0599
-1.500 0.2289 0.01961 0.00983 -0.0819 0.8461 0.0616
-1.250 0.2562 0.01903 0.00924 -0.0814 0.8347 0.0652
-1.000 0.2828 0.01850 0.00867 -0.0808 0.8231 0.0685
-0.750 0.3112 0.01797 0.00808 -0.0805 0.8126 0.0701
-0.500 0.3425 0.01735 0.00744 -0.0808 0.8032 0.0730
-0.250 0.3685 0.01699 0.00704 -0.0801 0.7905 0.0768
0.000 0.3963 0.01668 0.00665 -0.0797 0.7778 0.0827
0.250 0.4256 0.01631 0.00629 -0.0796 0.7646 0.0962
0.750 0.5387 0.01365 0.00585 -0.0907 0.7356 1.0000
1.000 0.5650 0.01366 0.00568 -0.0901 0.7183 1.0000
1.250 0.5908 0.01370 0.00554 -0.0893 0.6999 1.0000
1.500 0.6144 0.01379 0.00548 -0.0882 0.6798 1.0000
1.750 0.6373 0.01390 0.00545 -0.0870 0.6579 1.0000
2.000 0.6605 0.01403 0.00543 -0.0859 0.6351 1.0000
2.250 0.6833 0.01418 0.00543 -0.0846 0.6104 1.0000
2.500 0.7062 0.01436 0.00543 -0.0835 0.5861 1.0000
2.750 0.7292 0.01458 0.00546 -0.0823 0.5634 1.0000
3.000 0.7514 0.01485 0.00557 -0.0811 0.5417 1.0000
3.250 0.7737 0.01516 0.00571 -0.0799 0.5221 1.0000
3.500 0.7959 0.01549 0.00590 -0.0788 0.5042 1.0000
3.750 0.8178 0.01582 0.00614 -0.0776 0.4869 1.0000
4.000 0.8395 0.01616 0.00640 -0.0765 0.4700 1.0000
4.250 0.8610 0.01650 0.00667 -0.0753 0.4539 1.0000
4.500 0.8826 0.01685 0.00696 -0.0741 0.4388 1.0000
4.750 0.9043 0.01721 0.00728 -0.0730 0.4252 1.0000
5.250 0.9474 0.01796 0.00796 -0.0708 0.3997 1.0000
5.500 0.9690 0.01834 0.00835 -0.0697 0.3880 1.0000
5.750 0.9908 0.01875 0.00874 -0.0687 0.3780 1.0000
6.000 1.0125 0.01919 0.00915 -0.0677 0.3688 1.0000
6.250 1.0342 0.01961 0.00962 -0.0667 0.3593 1.0000
6.500 1.0559 0.02008 0.01008 -0.0657 0.3511 1.0000
6.750 1.0773 0.02053 0.01060 -0.0647 0.3421 1.0000
7.000 1.0983 0.02100 0.01111 -0.0636 0.3336 1.0000
7.250 1.1177 0.02148 0.01159 -0.0623 0.3236 1.0000
7.500 1.1337 0.02191 0.01207 -0.0604 0.3094 1.0000
7.750 1.1475 0.02236 0.01250 -0.0581 0.2936 1.0000
8.000 1.1633 0.02281 0.01303 -0.0563 0.2806 1.0000
8.250 1.1790 0.02328 0.01358 -0.0544 0.2683 1.0000
8.500 1.1938 0.02377 0.01414 -0.0524 0.2565 1.0000
8.750 1.2065 0.02428 0.01474 -0.0500 0.2442 1.0000
9.000 1.2164 0.02483 0.01533 -0.0473 0.2262 1.0000
9.250 1.2275 0.02546 0.01600 -0.0449 0.2094 1.0000
9.500 1.2392 0.02615 0.01674 -0.0426 0.1933 1.0000
9.750 1.2476 0.02704 0.01759 -0.0401 0.1660 1.0000
10.000 1.2504 0.02835 0.01869 -0.0371 0.1304 1.0000
10.250 1.2473 0.03027 0.02030 -0.0338 0.0871 1.0000
10.500 1.2296 0.03346 0.02297 -0.0296 0.0344 1.0000
10.750 1.2274 0.03554 0.02510 -0.0270 0.0285 1.0000
11.000 1.2276 0.03749 0.02717 -0.0248 0.0264 1.0000
11.250 1.2284 0.03946 0.02929 -0.0229 0.0253 1.0000
11.500 1.2280 0.04163 0.03165 -0.0212 0.0244 1.0000
11.750 1.2248 0.04416 0.03437 -0.0198 0.0235 1.0000
12.000 1.2200 0.04699 0.03738 -0.0186 0.0228 1.0000
12.250 1.2125 0.05028 0.04086 -0.0179 0.0221 1.0000
12.500 1.2034 0.05397 0.04474 -0.0176 0.0216 1.0000
12.750 1.1923 0.05819 0.04914 -0.0178 0.0213 1.0000
13.000 1.1768 0.06331 0.05444 -0.0188 0.0207 1.0000
13.250 1.1647 0.06836 0.05969 -0.0201 0.0206 1.0000
13.500 1.1484 0.07437 0.06588 -0.0221 0.0204 1.0000
13.750 1.1354 0.08010 0.07178 -0.0242 0.0203 1.0000
14.000 1.1221 0.08605 0.07788 -0.0264 0.0202 1.0000
14.250 1.1114 0.09168 0.08365 -0.0285 0.0199 1.0000
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Polar data table (+)
Polar graphs
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