GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 101 AIRFOIL (goe101-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.84 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe101-il-1000000.txt Download as CSV file: xf-goe101-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 101 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3738 0.08609 0.08455 -0.0177 1.0000 0.0110
-7.500 -0.3751 0.08339 0.08189 -0.0184 1.0000 0.0110
-7.250 -0.3728 0.07994 0.07846 -0.0215 1.0000 0.0111
-7.000 -0.3661 0.07656 0.07509 -0.0241 1.0000 0.0112
-6.750 -0.3586 0.07288 0.07142 -0.0269 1.0000 0.0112
-6.500 -0.3509 0.06911 0.06766 -0.0293 1.0000 0.0112
-6.250 -0.3220 0.06315 0.06164 -0.0376 0.9967 0.0112
-6.000 -0.3011 0.05776 0.05622 -0.0432 0.9906 0.0119
-5.750 -0.2709 0.05446 0.05288 -0.0484 0.9849 0.0126
-5.500 -0.2361 0.04996 0.04828 -0.0551 0.9780 0.0136
-5.250 -0.1866 0.04370 0.04182 -0.0639 0.9701 0.0152
-5.000 -0.1504 0.03854 0.03646 -0.0689 0.9563 0.0153
-4.750 -0.1218 0.03331 0.03099 -0.0717 0.9367 0.0153
-4.250 -0.0793 0.02075 0.01748 -0.0726 0.8898 0.0148
-4.000 -0.0568 0.01685 0.01304 -0.0718 0.8657 0.0163
-3.750 -0.0318 0.01790 0.01409 -0.0715 0.8366 0.0170
-3.500 -0.0071 0.01686 0.01279 -0.0709 0.8073 0.0184
-3.250 0.0180 0.01460 0.01005 -0.0699 0.7800 0.0198
-3.000 0.0430 0.01299 0.00800 -0.0692 0.7545 0.0219
-2.750 0.0686 0.01325 0.00827 -0.0691 0.7295 0.0234
-2.500 0.0958 0.01471 0.00978 -0.0690 0.7070 0.0279
-2.250 0.1223 0.01371 0.00851 -0.0684 0.6877 0.0283
-2.000 0.1490 0.01300 0.00758 -0.0680 0.6687 0.0286
-1.750 0.1748 0.01089 0.00512 -0.0675 0.6504 0.0300
-1.500 0.2011 0.01007 0.00417 -0.0672 0.6304 0.0310
-1.250 0.2277 0.00958 0.00354 -0.0668 0.6104 0.0309
-1.000 0.2544 0.00920 0.00304 -0.0664 0.5905 0.0306
-0.750 0.2809 0.00886 0.00260 -0.0661 0.5726 0.0308
-0.500 0.3074 0.00855 0.00222 -0.0657 0.5552 0.0314
-0.250 0.3340 0.00831 0.00189 -0.0654 0.5382 0.0321
0.000 0.3608 0.00815 0.00166 -0.0651 0.5233 0.0331
0.250 0.3878 0.00805 0.00150 -0.0649 0.5101 0.0341
0.500 0.4149 0.00798 0.00136 -0.0647 0.4969 0.0347
0.750 0.4420 0.00795 0.00126 -0.0645 0.4853 0.0351
1.000 0.4693 0.00790 0.00117 -0.0643 0.4764 0.0355
1.250 0.4966 0.00788 0.00112 -0.0641 0.4674 0.0365
1.500 0.5239 0.00789 0.00108 -0.0640 0.4584 0.0372
1.750 0.5513 0.00788 0.00105 -0.0638 0.4502 0.0382
2.000 0.5786 0.00792 0.00104 -0.0636 0.4423 0.0413
2.250 0.6102 0.00589 0.00125 -0.0652 0.4340 1.0000
2.500 0.6371 0.00600 0.00130 -0.0650 0.4267 1.0000
2.750 0.6641 0.00608 0.00136 -0.0648 0.4205 1.0000
3.000 0.6910 0.00619 0.00143 -0.0645 0.4145 1.0000
3.250 0.7182 0.00626 0.00150 -0.0644 0.4089 1.0000
3.500 0.7450 0.00637 0.00158 -0.0642 0.4024 1.0000
3.750 0.7721 0.00646 0.00168 -0.0640 0.3956 1.0000
4.000 0.7988 0.00659 0.00176 -0.0637 0.3830 1.0000
4.250 0.8255 0.00672 0.00186 -0.0635 0.3710 1.0000
4.500 0.8520 0.00688 0.00197 -0.0633 0.3521 1.0000
4.750 0.8777 0.00714 0.00212 -0.0630 0.3201 1.0000
5.000 0.9012 0.00769 0.00239 -0.0624 0.2589 1.0000
5.250 0.9234 0.00845 0.00281 -0.0617 0.1927 1.0000
5.500 0.9476 0.00894 0.00314 -0.0612 0.1585 1.0000
5.750 0.9694 0.00974 0.00361 -0.0604 0.0948 1.0000
6.000 0.9925 0.01037 0.00408 -0.0598 0.0627 1.0000
6.250 1.0135 0.01131 0.00477 -0.0588 0.0182 1.0000
6.500 1.0376 0.01181 0.00533 -0.0582 0.0144 1.0000
6.750 1.0622 0.01218 0.00575 -0.0577 0.0135 1.0000
7.000 1.0862 0.01264 0.00627 -0.0571 0.0123 1.0000
7.250 1.1096 0.01316 0.00684 -0.0564 0.0113 1.0000
7.500 1.1305 0.01400 0.00778 -0.0554 0.0102 1.0000
7.750 1.1504 0.01494 0.00884 -0.0542 0.0095 1.0000
8.000 1.1740 0.01533 0.00926 -0.0536 0.0090 1.0000
8.250 1.1953 0.01600 0.01001 -0.0527 0.0085 1.0000
8.500 1.2159 0.01672 0.01080 -0.0517 0.0080 1.0000
8.750 1.2356 0.01750 0.01165 -0.0506 0.0076 1.0000
9.000 1.2546 0.01831 0.01252 -0.0494 0.0073 1.0000
9.250 1.2719 0.01927 0.01354 -0.0481 0.0070 1.0000
9.500 1.2834 0.02081 0.01517 -0.0459 0.0066 1.0000
9.750 1.2872 0.02343 0.01796 -0.0428 0.0063 1.0000
10.000 1.3042 0.02427 0.01889 -0.0415 0.0062 1.0000
10.250 1.3192 0.02530 0.02002 -0.0399 0.0060 1.0000
10.500 1.3326 0.02641 0.02125 -0.0381 0.0058 1.0000
10.750 1.3429 0.02757 0.02251 -0.0359 0.0055 1.0000
11.000 1.3490 0.02890 0.02396 -0.0332 0.0053 1.0000
11.250 1.3541 0.03022 0.02539 -0.0306 0.0051 1.0000
11.500 1.3568 0.03199 0.02730 -0.0280 0.0050 1.0000
11.750 1.3595 0.03365 0.02909 -0.0259 0.0049 1.0000
12.000 1.3591 0.03589 0.03147 -0.0239 0.0049 1.0000
12.250 1.3580 0.03822 0.03395 -0.0223 0.0048 1.0000
12.500 1.3547 0.04095 0.03684 -0.0210 0.0048 1.0000
12.750 1.3538 0.04330 0.03930 -0.0205 0.0046 1.0000
13.000 1.3461 0.04698 0.04317 -0.0201 0.0046 1.0000
13.250 1.3411 0.05031 0.04663 -0.0204 0.0046 1.0000
13.500 1.3338 0.05420 0.05066 -0.0211 0.0045 1.0000
13.750 1.3249 0.05851 0.05513 -0.0224 0.0045 1.0000
14.000 1.3107 0.06400 0.06080 -0.0242 0.0045 1.0000
14.250 1.2926 0.07040 0.06740 -0.0268 0.0046 1.0000
14.500 1.2751 0.07703 0.07422 -0.0299 0.0046 1.0000
14.750 1.2384 0.08790 0.08539 -0.0353 0.0047 1.0000
15.000 1.2279 0.09406 0.09165 -0.0389 0.0047 1.0000
15.250 1.1959 0.10543 0.10326 -0.0455 0.0048 1.0000
15.500 1.1654 0.11754 0.11556 -0.0528 0.0049 1.0000
15.750 1.1549 0.12521 0.12332 -0.0577 0.0049 1.0000
16.000 1.1150 0.14231 0.14062 -0.0682 0.0052 1.0000
16.250 1.0836 0.15850 0.15694 -0.0778 0.0055 1.0000
16.500 1.0353 0.18285 0.18133 -0.0905 0.0062 1.0000
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Polar data table (+)
Polar graphs
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