GOE 512 AIRFOIL (goe512-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 512 AIRFOIL (goe512-il) Reynolds number: 200,000 Max Cl/Cd: 64.17 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe512-il-200000.txt Download as CSV file: xf-goe512-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 512 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3176 0.12497 0.12167 -0.0309 1.0000 0.0514
-10.500 -0.3412 0.12222 0.11900 -0.0334 1.0000 0.0520
-10.250 -0.3552 0.11940 0.11623 -0.0340 1.0000 0.0521
-10.000 -0.3393 0.11592 0.11277 -0.0298 1.0000 0.0530
-9.750 -0.3372 0.11390 0.11078 -0.0279 1.0000 0.0535
-9.500 -0.3368 0.11203 0.10895 -0.0260 1.0000 0.0543
-9.250 -0.3209 0.10844 0.10536 -0.0293 0.9972 0.0558
-9.000 -0.3087 0.10386 0.10077 -0.0357 0.9932 0.0594
-8.750 -0.3315 0.09637 0.09332 -0.0530 0.9839 0.0613
-8.500 -0.3068 0.09187 0.08883 -0.0514 0.9817 0.0624
-8.250 -0.2814 0.08958 0.08652 -0.0510 0.9770 0.0641
-8.000 -0.2644 0.08577 0.08270 -0.0556 0.9721 0.0663
-7.750 -0.2636 0.08180 0.07873 -0.0598 0.9629 0.0677
-7.500 -0.1522 0.06132 0.05835 -0.0760 0.9432 0.0765
-7.250 -0.1562 0.05809 0.05511 -0.0761 0.9322 0.0790
-7.000 -0.3137 0.04753 0.04341 -0.0755 0.9286 0.0512
-6.750 -0.3108 0.04305 0.03867 -0.0734 0.9184 0.0504
-6.500 -0.2993 0.03740 0.03237 -0.0728 0.9129 0.0503
-6.250 -0.2930 0.03399 0.02848 -0.0694 0.9024 0.0505
-6.000 -0.2686 0.03067 0.02451 -0.0689 0.8980 0.0512
-5.750 -0.2543 0.02850 0.02188 -0.0662 0.8891 0.0527
-5.500 -0.2218 0.02706 0.02050 -0.0673 0.8847 0.0557
-5.250 -0.1859 0.02536 0.01850 -0.0685 0.8821 0.0584
-5.000 -0.1652 0.02430 0.01711 -0.0665 0.8728 0.0606
-4.750 -0.1302 0.02248 0.01517 -0.0677 0.8692 0.0643
-4.500 -0.0889 0.02121 0.01378 -0.0698 0.8669 0.0684
-4.250 -0.0611 0.02053 0.01289 -0.0692 0.8591 0.0720
-4.000 -0.0234 0.01893 0.01132 -0.0709 0.8544 0.0769
-3.750 0.0223 0.01795 0.01025 -0.0740 0.8514 0.0832
-3.500 0.0556 0.01689 0.00922 -0.0747 0.8435 0.0889
-3.250 0.0980 0.01610 0.00840 -0.0772 0.8370 0.0974
-3.000 0.1363 0.01526 0.00763 -0.0790 0.8289 0.1076
-2.750 0.1746 0.01460 0.00701 -0.0807 0.8196 0.1246
-2.500 0.2051 0.01395 0.00656 -0.0810 0.8079 0.1621
-2.250 0.2391 0.01405 0.00682 -0.0818 0.7961 0.2463
-2.000 0.2721 0.01426 0.00684 -0.0823 0.7832 0.2718
-1.750 0.2997 0.01430 0.00674 -0.0818 0.7678 0.2878
-1.500 0.3256 0.01427 0.00657 -0.0811 0.7512 0.3014
-1.250 0.3500 0.01425 0.00641 -0.0800 0.7339 0.3137
-1.000 0.3746 0.01408 0.00619 -0.0792 0.7158 0.3258
-0.750 0.3992 0.01393 0.00597 -0.0783 0.6972 0.3358
-0.500 0.4225 0.01390 0.00579 -0.0771 0.6784 0.3459
-0.250 0.4466 0.01377 0.00561 -0.0762 0.6597 0.3567
0.000 0.4696 0.01370 0.00547 -0.0750 0.6420 0.3668
0.250 0.4920 0.01371 0.00539 -0.0738 0.6257 0.3766
0.500 0.5140 0.01368 0.00533 -0.0725 0.6102 0.3834
0.750 0.5355 0.01371 0.00530 -0.0711 0.5956 0.3895
1.000 0.5568 0.01377 0.00528 -0.0696 0.5821 0.3962
1.250 0.5751 0.01376 0.00527 -0.0676 0.5689 0.4047
1.500 0.5925 0.01376 0.00530 -0.0654 0.5563 0.4168
1.750 0.6101 0.01373 0.00533 -0.0632 0.5450 0.4387
2.000 0.7541 0.01367 0.00643 -0.0877 0.5227 0.9466
2.250 0.7914 0.01410 0.00674 -0.0895 0.5101 0.9667
2.500 0.8446 0.01455 0.00705 -0.0948 0.4966 0.9823
2.750 0.9094 0.01487 0.00718 -0.1028 0.4831 0.9937
3.000 0.9581 0.01503 0.00723 -0.1075 0.4708 1.0000
3.250 0.9757 0.01525 0.00741 -0.1056 0.4616 1.0000
3.500 0.9940 0.01552 0.00756 -0.1037 0.4530 1.0000
3.750 1.0107 0.01575 0.00777 -0.1016 0.4440 1.0000
4.000 1.0295 0.01606 0.00795 -0.0999 0.4354 1.0000
4.250 1.0443 0.01628 0.00820 -0.0974 0.4261 1.0000
4.500 1.0630 0.01663 0.00840 -0.0957 0.4176 1.0000
4.750 1.0760 0.01685 0.00866 -0.0928 0.4081 1.0000
5.000 1.0927 0.01719 0.00891 -0.0907 0.3993 1.0000
5.250 1.1047 0.01743 0.00916 -0.0877 0.3897 1.0000
5.500 1.1194 0.01775 0.00943 -0.0852 0.3810 1.0000
5.750 1.1315 0.01802 0.00969 -0.0822 0.3723 1.0000
6.000 1.1458 0.01836 0.00999 -0.0797 0.3643 1.0000
6.250 1.1573 0.01863 0.01026 -0.0766 0.3564 1.0000
6.500 1.1722 0.01899 0.01055 -0.0742 0.3497 1.0000
6.750 1.1813 0.01925 0.01085 -0.0707 0.3427 1.0000
7.000 1.1962 0.01959 0.01113 -0.0683 0.3370 1.0000
7.250 1.2086 0.01993 0.01150 -0.0655 0.3312 1.0000
7.500 1.2200 0.02022 0.01181 -0.0625 0.3256 1.0000
7.750 1.2374 0.02062 0.01213 -0.0608 0.3209 1.0000
8.000 1.2520 0.02101 0.01257 -0.0585 0.3163 1.0000
8.250 1.2631 0.02133 0.01294 -0.0556 0.3112 1.0000
8.500 1.2776 0.02169 0.01327 -0.0533 0.3068 1.0000
8.750 1.2933 0.02212 0.01369 -0.0514 0.3021 1.0000
9.000 1.3042 0.02250 0.01417 -0.0486 0.2976 1.0000
9.250 1.3180 0.02289 0.01458 -0.0463 0.2935 1.0000
9.500 1.3384 0.02338 0.01500 -0.0454 0.2899 1.0000
9.750 1.3556 0.02390 0.01560 -0.0439 0.2866 1.0000
10.000 1.3685 0.02438 0.01619 -0.0416 0.2834 1.0000
10.250 1.3833 0.02487 0.01675 -0.0397 0.2800 1.0000
10.500 1.4009 0.02537 0.01726 -0.0383 0.2769 1.0000
10.750 1.4248 0.02597 0.01780 -0.0382 0.2727 1.0000
11.000 1.4274 0.02650 0.01850 -0.0343 0.2691 1.0000
11.250 1.4348 0.02701 0.01910 -0.0313 0.2647 1.0000
11.500 1.4476 0.02750 0.01954 -0.0294 0.2599 1.0000
11.750 1.4584 0.02817 0.02027 -0.0272 0.2556 1.0000
12.000 1.4620 0.02886 0.02111 -0.0240 0.2515 1.0000
12.250 1.4707 0.02948 0.02178 -0.0216 0.2473 1.0000
12.500 1.4927 0.03008 0.02227 -0.0213 0.2424 1.0000
12.750 1.4901 0.03098 0.02340 -0.0175 0.2392 1.0000
13.000 1.4936 0.03186 0.02441 -0.0148 0.2353 1.0000
13.250 1.5001 0.03265 0.02524 -0.0126 0.2309 1.0000
13.500 1.5125 0.03345 0.02601 -0.0112 0.2262 1.0000
13.750 1.5092 0.03470 0.02748 -0.0081 0.2226 1.0000
14.000 1.5106 0.03585 0.02875 -0.0058 0.2184 1.0000
14.250 1.5165 0.03685 0.02976 -0.0041 0.2141 1.0000
14.500 1.5196 0.03815 0.03115 -0.0022 0.2099 1.0000
14.750 1.5135 0.03993 0.03313 0.0001 0.2053 1.0000
15.000 1.5125 0.04152 0.03481 0.0018 0.2008 1.0000
15.250 1.5150 0.04303 0.03632 0.0032 0.1961 1.0000
15.500 1.5091 0.04533 0.03886 0.0046 0.1920 1.0000
15.750 1.5035 0.04772 0.04138 0.0057 0.1867 1.0000
16.000 1.5030 0.04979 0.04346 0.0065 0.1820 1.0000
16.250 1.4935 0.05303 0.04695 0.0070 0.1760 1.0000
16.500 1.4872 0.05603 0.05002 0.0073 0.1702 1.0000
16.750 1.4798 0.05939 0.05357 0.0073 0.1637 1.0000
17.000 1.4679 0.06341 0.05766 0.0070 0.1561 1.0000
17.250 1.4569 0.06754 0.06193 0.0065 0.1479 1.0000
17.500 1.4420 0.07225 0.06669 0.0057 0.1403 1.0000
17.750 1.4232 0.07762 0.07211 0.0047 0.1319 1.0000
18.000 1.4052 0.08304 0.07761 0.0035 0.1245 1.0000
18.500 1.3631 0.09510 0.08980 0.0003 0.1111 1.0000
18.750 1.3375 0.10200 0.09675 -0.0017 0.1041 1.0000
19.000 1.3152 0.10856 0.10339 -0.0038 0.0973 1.0000
19.250 1.2943 0.11500 0.10991 -0.0061 0.0914 1.0000
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