GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il) Reynolds number: 200,000 Max Cl/Cd: 72.29 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe143-il-200000.txt Download as CSV file: xf-goe143-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 143 (MVA H.20) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4318 0.11272 0.10913 -0.0041 1.0000 0.0400
-9.000 -0.4327 0.11053 0.10699 -0.0090 1.0000 0.0404
-8.750 -0.4310 0.10767 0.10417 -0.0129 1.0000 0.0406
-8.500 -0.4286 0.10446 0.10101 -0.0167 1.0000 0.0407
-8.250 -0.4185 0.09790 0.09446 -0.0132 1.0000 0.0415
-8.000 -0.4053 0.09441 0.09096 -0.0110 1.0000 0.0427
-7.750 -0.3979 0.09142 0.08799 -0.0116 1.0000 0.0439
-7.500 -0.3925 0.08842 0.08502 -0.0130 1.0000 0.0450
-7.250 -0.3855 0.08518 0.08181 -0.0155 1.0000 0.0464
-7.000 -0.3756 0.08163 0.07828 -0.0200 1.0000 0.0484
-6.750 -0.3520 0.07748 0.07405 -0.0362 1.0000 0.0507
-6.500 -0.3344 0.07336 0.06982 -0.0423 1.0000 0.0509
-6.250 -0.3353 0.06763 0.06421 -0.0397 1.0000 0.0520
-6.000 -0.3293 0.06529 0.06194 -0.0365 1.0000 0.0531
-5.750 -0.3199 0.06278 0.05945 -0.0359 1.0000 0.0545
-5.500 -0.3090 0.05998 0.05664 -0.0366 1.0000 0.0563
-5.250 -0.2966 0.05699 0.05359 -0.0381 1.0000 0.0589
-4.750 -0.2609 0.04877 0.04497 -0.0448 1.0000 0.0648
-4.500 -0.2502 0.04681 0.04308 -0.0435 0.9994 0.0663
-4.250 -0.2107 0.04358 0.03974 -0.0484 0.9952 0.0706
-4.000 -0.1589 0.03858 0.03422 -0.0564 0.9905 0.0785
-3.750 -0.1236 0.03613 0.03181 -0.0596 0.9858 0.0825
-3.500 -0.0753 0.03283 0.02798 -0.0651 0.9811 0.0924
-3.250 -0.0391 0.03037 0.02555 -0.0681 0.9751 0.0962
-3.000 0.0062 0.02791 0.02274 -0.0725 0.9711 0.1075
-2.750 0.0471 0.02621 0.02073 -0.0756 0.9645 0.1203
-2.500 0.0861 0.02409 0.01864 -0.0785 0.9587 0.1270
-2.250 0.1237 0.02240 0.01679 -0.0809 0.9508 0.1406
-2.000 0.1702 0.01910 0.01250 -0.0819 0.9432 0.0931
-1.750 0.2042 0.01736 0.01054 -0.0824 0.9319 0.0841
-1.500 0.2367 0.01602 0.00892 -0.0825 0.9196 0.0814
-1.250 0.2664 0.01510 0.00784 -0.0821 0.9054 0.0815
-1.000 0.2939 0.01449 0.00716 -0.0814 0.8894 0.0844
-0.750 0.3207 0.01395 0.00650 -0.0804 0.8723 0.0870
-0.500 0.3469 0.01342 0.00585 -0.0793 0.8544 0.0886
-0.250 0.3728 0.01309 0.00538 -0.0781 0.8359 0.0905
0.000 0.3983 0.01242 0.00475 -0.0772 0.8149 0.0941
0.250 0.4240 0.01217 0.00447 -0.0763 0.7932 0.1006
0.500 0.4499 0.01188 0.00413 -0.0754 0.7696 0.1063
0.750 0.4759 0.01159 0.00382 -0.0746 0.7449 0.1141
1.000 0.5023 0.01134 0.00353 -0.0740 0.7165 0.1266
1.250 0.5287 0.01095 0.00331 -0.0735 0.6866 0.1923
1.500 0.5504 0.00919 0.00318 -0.0716 0.6562 1.0000
1.750 0.5764 0.00943 0.00314 -0.0709 0.6231 1.0000
2.000 0.6026 0.00970 0.00316 -0.0703 0.5914 1.0000
2.250 0.6288 0.00999 0.00323 -0.0698 0.5640 1.0000
2.500 0.6554 0.01026 0.00333 -0.0694 0.5393 1.0000
2.750 0.6818 0.01056 0.00345 -0.0691 0.5175 1.0000
3.000 0.7084 0.01082 0.00360 -0.0687 0.4958 1.0000
3.250 0.7349 0.01110 0.00375 -0.0684 0.4768 1.0000
3.500 0.7616 0.01138 0.00393 -0.0681 0.4607 1.0000
3.750 0.7884 0.01165 0.00413 -0.0678 0.4458 1.0000
4.000 0.8151 0.01191 0.00437 -0.0676 0.4315 1.0000
4.250 0.8417 0.01218 0.00459 -0.0673 0.4174 1.0000
4.500 0.8683 0.01244 0.00483 -0.0670 0.4031 1.0000
4.750 0.8947 0.01270 0.00509 -0.0667 0.3884 1.0000
5.000 0.9210 0.01296 0.00534 -0.0664 0.3729 1.0000
5.250 0.9470 0.01323 0.00560 -0.0660 0.3559 1.0000
5.500 0.9729 0.01350 0.00587 -0.0657 0.3361 1.0000
5.750 0.9983 0.01381 0.00617 -0.0653 0.3106 1.0000
6.000 1.0227 0.01424 0.00648 -0.0648 0.2711 1.0000
6.250 1.0453 0.01496 0.00693 -0.0641 0.2232 1.0000
6.500 1.0679 0.01573 0.00749 -0.0635 0.1929 1.0000
6.750 1.0913 0.01638 0.00808 -0.0629 0.1753 1.0000
7.000 1.1147 0.01701 0.00865 -0.0624 0.1624 1.0000
7.250 1.1379 0.01764 0.00924 -0.0619 0.1524 1.0000
7.500 1.1622 0.01810 0.00978 -0.0614 0.1437 1.0000
7.750 1.1857 0.01863 0.01035 -0.0609 0.1339 1.0000
8.000 1.2094 0.01910 0.01085 -0.0604 0.1212 1.0000
8.250 1.2337 0.01951 0.01129 -0.0600 0.1050 1.0000
8.500 1.2569 0.02012 0.01181 -0.0593 0.0768 1.0000
8.750 1.2728 0.02167 0.01300 -0.0579 0.0413 1.0000
9.000 1.2897 0.02303 0.01444 -0.0564 0.0369 1.0000
9.250 1.3059 0.02436 0.01592 -0.0549 0.0344 1.0000
9.500 1.3215 0.02565 0.01739 -0.0533 0.0325 1.0000
9.750 1.3341 0.02714 0.01903 -0.0515 0.0307 1.0000
10.000 1.3436 0.02881 0.02084 -0.0494 0.0296 1.0000
10.250 1.3497 0.03069 0.02280 -0.0470 0.0287 1.0000
10.500 1.3529 0.03276 0.02493 -0.0442 0.0280 1.0000
10.750 1.3555 0.03506 0.02728 -0.0413 0.0275 1.0000
11.000 1.3635 0.03712 0.02942 -0.0392 0.0271 1.0000
11.250 1.3720 0.03879 0.03125 -0.0373 0.0266 1.0000
11.500 1.3793 0.04060 0.03322 -0.0354 0.0260 1.0000
11.750 1.3857 0.04262 0.03540 -0.0338 0.0253 1.0000
12.000 1.3917 0.04486 0.03780 -0.0322 0.0248 1.0000
12.250 1.3970 0.04732 0.04045 -0.0307 0.0245 1.0000
12.500 1.3996 0.05004 0.04336 -0.0294 0.0243 1.0000
12.750 1.3998 0.05302 0.04656 -0.0282 0.0242 1.0000
13.000 1.3973 0.05632 0.05008 -0.0274 0.0242 1.0000
13.250 1.3918 0.05999 0.05399 -0.0269 0.0242 1.0000
13.500 1.3836 0.06407 0.05831 -0.0269 0.0243 1.0000
13.750 1.3726 0.06862 0.06312 -0.0275 0.0244 1.0000
14.000 1.3593 0.07369 0.06843 -0.0289 0.0246 1.0000
14.250 1.3440 0.07929 0.07426 -0.0309 0.0248 1.0000
14.500 1.3269 0.08546 0.08066 -0.0336 0.0250 1.0000
14.750 1.3082 0.09214 0.08756 -0.0369 0.0252 1.0000
15.000 1.2884 0.09939 0.09502 -0.0409 0.0254 1.0000
15.250 1.2675 0.10729 0.10311 -0.0456 0.0256 1.0000
15.500 1.2461 0.11578 0.11178 -0.0509 0.0259 1.0000
15.750 1.2237 0.12503 0.12120 -0.0568 0.0261 1.0000
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Polar data table (+)
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