GOE 11K AIRFOIL (goe11k-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 11K AIRFOIL (goe11k-il) Reynolds number: 200,000 Max Cl/Cd: 72.42 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe11k-il-200000.txt Download as CSV file: xf-goe11k-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 11K 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5211 0.10237 0.09895 -0.0316 1.0000 0.0458
-8.500 -0.5360 0.09999 0.09663 -0.0307 1.0000 0.0458
-8.250 -0.5463 0.09693 0.09359 -0.0309 1.0000 0.0459
-8.000 -0.5556 0.09087 0.08759 -0.0283 1.0000 0.0466
-7.750 -0.5562 0.08794 0.08468 -0.0254 1.0000 0.0473
-7.500 -0.5589 0.08513 0.08189 -0.0239 1.0000 0.0477
-7.250 -0.5614 0.08233 0.07909 -0.0227 1.0000 0.0483
-7.000 -0.5634 0.07941 0.07617 -0.0218 1.0000 0.0492
-6.750 -0.5648 0.07619 0.07294 -0.0216 1.0000 0.0500
-6.500 -0.5648 0.07273 0.06944 -0.0218 1.0000 0.0511
-6.250 -0.5627 0.06899 0.06565 -0.0223 1.0000 0.0527
-6.000 -0.5579 0.06489 0.06145 -0.0233 1.0000 0.0545
-5.750 -0.5441 0.06042 0.05643 -0.0265 1.0000 0.0582
-5.500 -0.5352 0.05688 0.05259 -0.0257 1.0000 0.0585
-5.250 -0.5338 0.05023 0.04608 -0.0252 1.0000 0.0605
-5.000 -0.5224 0.04840 0.04426 -0.0238 1.0000 0.0626
-4.750 -0.5041 0.04551 0.04119 -0.0239 0.9991 0.0654
-4.500 -0.4746 0.04047 0.03535 -0.0261 0.9957 0.0737
-4.250 -0.4500 0.03754 0.03238 -0.0271 0.9931 0.0758
-4.000 -0.4250 0.03557 0.03025 -0.0274 0.9901 0.0811
-3.750 -0.3994 0.03442 0.02864 -0.0279 0.9871 0.1022
-3.500 -0.3736 0.03192 0.02612 -0.0284 0.9854 0.1058
-3.000 -0.3191 0.02227 0.01448 -0.0240 0.9814 0.0677
-2.750 -0.2913 0.02153 0.01341 -0.0238 0.9783 0.0735
-2.500 -0.2628 0.02065 0.01251 -0.0242 0.9760 0.0788
-2.250 -0.2317 0.02045 0.01217 -0.0250 0.9741 0.0850
-2.000 -0.2053 0.01978 0.01143 -0.0248 0.9717 0.0891
-1.750 -0.1818 0.01940 0.01107 -0.0242 0.9681 0.0942
-1.500 -0.1538 0.01918 0.01080 -0.0244 0.9652 0.0986
-1.250 -0.1243 0.01888 0.01050 -0.0248 0.9629 0.1026
-1.000 -0.0937 0.01881 0.01050 -0.0256 0.9611 0.1096
-0.750 -0.0736 0.01863 0.01028 -0.0242 0.9572 0.1142
-0.500 -0.0489 0.01842 0.01016 -0.0238 0.9536 0.1215
-0.250 -0.0186 0.01836 0.01016 -0.0245 0.9506 0.1349
0.000 0.0153 0.01775 0.01032 -0.0260 0.9480 0.3041
0.250 0.1339 0.01625 0.01073 -0.0463 0.9527 1.0000
0.500 0.1711 0.01647 0.01086 -0.0484 0.9494 1.0000
0.750 0.1981 0.01661 0.01094 -0.0485 0.9442 1.0000
1.000 0.2294 0.01672 0.01101 -0.0494 0.9392 1.0000
1.250 0.2683 0.01688 0.01115 -0.0518 0.9361 1.0000
1.500 0.2927 0.01698 0.01124 -0.0513 0.9297 1.0000
1.750 0.3371 0.01687 0.01113 -0.0545 0.9238 1.0000
2.000 0.3845 0.01634 0.01065 -0.0578 0.9127 1.0000
2.250 0.4386 0.01569 0.01005 -0.0624 0.9044 1.0000
2.500 0.5111 0.01425 0.00872 -0.0699 0.8944 1.0000
2.750 0.5798 0.01244 0.00704 -0.0763 0.8805 1.0000
3.000 0.6356 0.01129 0.00601 -0.0807 0.8642 1.0000
3.250 0.6715 0.01065 0.00546 -0.0813 0.8375 1.0000
3.500 0.7394 0.01021 0.00414 -0.0875 0.5862 1.0000
3.750 0.7194 0.01186 0.00464 -0.0773 0.3939 1.0000
4.000 0.7090 0.01367 0.00527 -0.0699 0.1797 1.0000
4.250 0.7200 0.01463 0.00587 -0.0666 0.1312 1.0000
4.500 0.7353 0.01528 0.00644 -0.0641 0.1159 1.0000
4.750 0.7527 0.01582 0.00697 -0.0619 0.1054 1.0000
5.000 0.7696 0.01650 0.00762 -0.0597 0.0966 1.0000
5.250 0.7864 0.01739 0.00842 -0.0577 0.0878 1.0000
5.500 0.8066 0.01796 0.00908 -0.0561 0.0795 1.0000
5.750 0.8281 0.01914 0.01022 -0.0550 0.0716 1.0000
6.000 0.8498 0.01992 0.01101 -0.0538 0.0638 1.0000
6.250 0.8774 0.02138 0.01254 -0.0539 0.0568 1.0000
6.500 0.9020 0.02241 0.01362 -0.0532 0.0514 1.0000
6.750 0.9313 0.02430 0.01562 -0.0537 0.0464 1.0000
7.000 0.9556 0.02549 0.01702 -0.0528 0.0430 1.0000
7.250 0.9795 0.02693 0.01862 -0.0520 0.0404 1.0000
7.500 1.0028 0.02900 0.02073 -0.0516 0.0378 1.0000
7.750 1.0204 0.03106 0.02321 -0.0495 0.0358 1.0000
8.000 1.0366 0.03364 0.02622 -0.0470 0.0348 1.0000
8.250 1.0481 0.03679 0.02982 -0.0438 0.0343 1.0000
8.500 1.0537 0.04039 0.03387 -0.0398 0.0343 1.0000
8.750 1.0552 0.04420 0.03808 -0.0355 0.0349 1.0000
9.000 1.0522 0.04806 0.04231 -0.0308 0.0352 1.0000
9.250 1.0474 0.05165 0.04622 -0.0261 0.0353 1.0000
9.500 1.0390 0.05548 0.05033 -0.0215 0.0357 1.0000
9.750 1.0284 0.05942 0.05448 -0.0171 0.0361 1.0000
10.000 0.9514 0.07144 0.06740 -0.0050 0.0554 1.0000
10.250 0.9289 0.07505 0.07113 -0.0016 0.0555 1.0000
10.500 0.9056 0.07925 0.07542 0.0001 0.0559 1.0000
10.750 0.8828 0.08427 0.08052 0.0003 0.0570 1.0000
11.000 0.8576 0.09044 0.08678 -0.0021 0.0572 1.0000
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Polar data table (+)
Polar graphs
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