GOE 512 AIRFOIL (goe512-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 512 AIRFOIL (goe512-il) Reynolds number: 100,000 Max Cl/Cd: 47.37 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe512-il-100000-n5.txt Download as CSV file: xf-goe512-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2860 0.09343 0.08890 -0.0518 0.9810 0.0348
-8.750 -0.2804 0.08899 0.08448 -0.0559 0.9755 0.0353
-8.500 -0.2797 0.08442 0.07992 -0.0600 0.9684 0.0358
-8.250 -0.2823 0.07914 0.07464 -0.0653 0.9611 0.0361
-8.000 -0.2918 0.07415 0.06965 -0.0675 0.9499 0.0363
-7.750 -0.2974 0.06821 0.06364 -0.0704 0.9393 0.0370
-7.500 -0.3046 0.05868 0.05387 -0.0751 0.9305 0.0373
-7.250 -0.3252 0.04920 0.04389 -0.0749 0.9178 0.0374
-7.000 -0.3348 0.04318 0.03724 -0.0723 0.9063 0.0382
-6.750 -0.3279 0.03741 0.03041 -0.0711 0.9002 0.0401
-6.500 -0.3138 0.03637 0.02937 -0.0690 0.8895 0.0414
-6.250 -0.2842 0.03475 0.02754 -0.0698 0.8843 0.0439
-6.000 -0.2704 0.03264 0.02497 -0.0673 0.8735 0.0459
-5.750 -0.2487 0.03070 0.02258 -0.0661 0.8649 0.0486
-5.500 -0.2208 0.02956 0.02136 -0.0661 0.8575 0.0513
-5.250 -0.1967 0.02828 0.01980 -0.0651 0.8493 0.0545
-5.000 -0.1695 0.02695 0.01813 -0.0646 0.8425 0.0579
-4.750 -0.1350 0.02577 0.01692 -0.0657 0.8388 0.0618
-4.500 -0.1154 0.02507 0.01604 -0.0639 0.8278 0.0658
-4.250 -0.0793 0.02386 0.01464 -0.0650 0.8234 0.0698
-4.000 -0.0581 0.02316 0.01394 -0.0636 0.8128 0.0733
-3.750 -0.0216 0.02228 0.01292 -0.0648 0.8074 0.0793
-3.500 0.0014 0.02163 0.01220 -0.0636 0.7966 0.0833
-3.250 0.0387 0.02081 0.01134 -0.0651 0.7904 0.0908
-3.000 0.0626 0.02031 0.01080 -0.0640 0.7789 0.0974
-2.750 0.1009 0.01965 0.01009 -0.0657 0.7713 0.1089
-2.500 0.1286 0.01918 0.00971 -0.0654 0.7599 0.1255
-2.250 0.1602 0.01868 0.00936 -0.0660 0.7491 0.1596
-2.000 0.1982 0.01851 0.00935 -0.0676 0.7392 0.2166
-1.750 0.2238 0.01864 0.00931 -0.0668 0.7257 0.2475
-1.500 0.2522 0.01870 0.00919 -0.0665 0.7128 0.2680
-1.250 0.2831 0.01870 0.00898 -0.0668 0.7006 0.2862
-1.000 0.3170 0.01855 0.00872 -0.0678 0.6885 0.3028
-0.750 0.3481 0.01839 0.00847 -0.0682 0.6749 0.3182
-0.500 0.3790 0.01825 0.00827 -0.0687 0.6612 0.3331
-0.250 0.4121 0.01813 0.00806 -0.0696 0.6471 0.3451
0.000 0.4460 0.01802 0.00786 -0.0707 0.6320 0.3532
0.250 0.4757 0.01801 0.00771 -0.0709 0.6157 0.3610
0.500 0.5018 0.01798 0.00759 -0.0705 0.5985 0.3687
0.750 0.5253 0.01800 0.00752 -0.0695 0.5822 0.3781
1.000 0.5472 0.01800 0.00747 -0.0682 0.5669 0.3882
1.250 0.5697 0.01802 0.00744 -0.0671 0.5538 0.3994
1.500 0.5895 0.01805 0.00749 -0.0655 0.5411 0.4131
1.750 0.6086 0.01797 0.00753 -0.0638 0.5300 0.4488
2.250 0.7845 0.01832 0.00873 -0.0885 0.4959 0.9753
2.500 0.8261 0.01865 0.00891 -0.0915 0.4836 0.9882
3.000 0.8945 0.01924 0.00926 -0.0947 0.4620 1.0000
3.250 0.9122 0.01951 0.00940 -0.0928 0.4540 1.0000
3.500 0.9289 0.01978 0.00964 -0.0907 0.4454 1.0000
4.000 0.9625 0.02037 0.01010 -0.0866 0.4296 1.0000
4.250 0.9793 0.02069 0.01032 -0.0845 0.4221 1.0000
4.500 0.9947 0.02100 0.01061 -0.0822 0.4140 1.0000
4.750 1.0101 0.02133 0.01088 -0.0800 0.4062 1.0000
5.000 1.0249 0.02166 0.01119 -0.0776 0.3984 1.0000
5.250 1.0389 0.02200 0.01150 -0.0751 0.3905 1.0000
5.500 1.0536 0.02235 0.01182 -0.0727 0.3834 1.0000
5.750 1.0656 0.02268 0.01217 -0.0698 0.3759 1.0000
6.000 1.0798 0.02304 0.01245 -0.0674 0.3696 1.0000
6.250 1.0902 0.02338 0.01285 -0.0643 0.3620 1.0000
6.500 1.1028 0.02375 0.01321 -0.0616 0.3557 1.0000
6.750 1.1155 0.02414 0.01360 -0.0590 0.3494 1.0000
7.000 1.1275 0.02455 0.01403 -0.0563 0.3428 1.0000
7.250 1.1411 0.02496 0.01438 -0.0540 0.3374 1.0000
7.500 1.1527 0.02542 0.01492 -0.0513 0.3309 1.0000
7.750 1.1648 0.02587 0.01538 -0.0488 0.3251 1.0000
8.000 1.1788 0.02634 0.01582 -0.0466 0.3203 1.0000
8.250 1.1914 0.02687 0.01643 -0.0443 0.3149 1.0000
8.500 1.2050 0.02740 0.01699 -0.0422 0.3104 1.0000
8.750 1.2204 0.02791 0.01747 -0.0405 0.3067 1.0000
9.000 1.2335 0.02853 0.01817 -0.0384 0.3023 1.0000
9.250 1.2459 0.02914 0.01886 -0.0363 0.2978 1.0000
9.500 1.2593 0.02974 0.01949 -0.0343 0.2939 1.0000
9.750 1.2753 0.03030 0.02001 -0.0328 0.2905 1.0000
10.000 1.2838 0.03108 0.02094 -0.0303 0.2859 1.0000
10.250 1.2936 0.03181 0.02174 -0.0281 0.2815 1.0000
10.500 1.3051 0.03247 0.02242 -0.0261 0.2773 1.0000
10.750 1.3181 0.03319 0.02317 -0.0244 0.2736 1.0000
11.000 1.3248 0.03415 0.02428 -0.0220 0.2695 1.0000
11.250 1.3347 0.03504 0.02527 -0.0201 0.2661 1.0000
11.500 1.3467 0.03587 0.02617 -0.0185 0.2629 1.0000
11.750 1.3623 0.03658 0.02689 -0.0173 0.2600 1.0000
12.000 1.3707 0.03765 0.02809 -0.0155 0.2569 1.0000
12.250 1.3741 0.03894 0.02957 -0.0132 0.2536 1.0000
12.500 1.3799 0.04015 0.03090 -0.0113 0.2502 1.0000
12.750 1.3893 0.04119 0.03203 -0.0097 0.2470 1.0000
13.000 1.4043 0.04202 0.03289 -0.0087 0.2441 1.0000
13.250 1.4091 0.04340 0.03441 -0.0070 0.2410 1.0000
13.500 1.4023 0.04546 0.03669 -0.0046 0.2374 1.0000
13.750 1.4010 0.04725 0.03863 -0.0028 0.2336 1.0000
14.000 1.4068 0.04846 0.03987 -0.0014 0.2292 1.0000
14.250 1.4084 0.05006 0.04154 0.0000 0.2248 1.0000
14.500 1.3936 0.05315 0.04487 0.0018 0.2211 1.0000
14.750 1.3839 0.05588 0.04775 0.0031 0.2161 1.0000
15.000 1.3930 0.05687 0.04869 0.0039 0.2109 1.0000
15.250 1.3769 0.06069 0.05274 0.0047 0.2076 1.0000
15.500 1.3533 0.06559 0.05789 0.0050 0.2035 1.0000
15.750 1.3414 0.06939 0.06182 0.0051 0.1993 1.0000
16.000 1.3528 0.07031 0.06272 0.0055 0.1950 1.0000
16.250 1.3171 0.07758 0.07027 0.0045 0.1919 1.0000
16.500 1.2572 0.08900 0.08198 0.0017 0.1891 1.0000
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Polar data table (+)
Polar graphs
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