GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il) Reynolds number: 200,000 Max Cl/Cd: 70.4 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe134-il-200000.txt Download as CSV file: xf-goe134-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 134 (MVA H.12) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3803 0.09417 0.09070 -0.0263 1.0000 0.0325
-7.750 -0.3878 0.09125 0.08785 -0.0307 1.0000 0.0329
-7.500 -0.3876 0.08752 0.08414 -0.0365 1.0000 0.0331
-7.250 -0.3852 0.08368 0.08024 -0.0403 1.0000 0.0332
-7.000 -0.3847 0.07924 0.07590 -0.0367 1.0000 0.0337
-6.750 -0.3817 0.07643 0.07314 -0.0342 1.0000 0.0342
-6.500 -0.3781 0.07364 0.07037 -0.0333 1.0000 0.0348
-6.250 -0.3737 0.07072 0.06745 -0.0333 1.0000 0.0355
-6.000 -0.3679 0.06763 0.06434 -0.0338 1.0000 0.0365
-5.750 -0.3599 0.06435 0.06103 -0.0347 1.0000 0.0377
-5.500 -0.3470 0.06075 0.05731 -0.0367 1.0000 0.0397
-5.250 -0.3268 0.05596 0.05207 -0.0407 1.0000 0.0418
-5.000 -0.3224 0.05284 0.04910 -0.0391 1.0000 0.0427
-4.750 -0.3013 0.05016 0.04642 -0.0405 0.9979 0.0447
-4.500 -0.2428 0.04817 0.04359 -0.0478 0.9930 0.0517
-4.250 -0.2162 0.04133 0.03696 -0.0518 0.9886 0.0540
-4.000 -0.1770 0.03850 0.03403 -0.0561 0.9845 0.0588
-3.750 -0.1357 0.03507 0.03023 -0.0602 0.9785 0.0673
-3.500 -0.0915 0.03286 0.02757 -0.0643 0.9734 0.0795
-3.250 -0.0526 0.03007 0.02485 -0.0680 0.9691 0.0864
-3.000 -0.0132 0.02779 0.02235 -0.0712 0.9617 0.1000
-2.750 0.0310 0.02587 0.02015 -0.0754 0.9577 0.1258
-1.250 0.2491 0.01611 0.00863 -0.0792 0.8802 0.0739
-1.000 0.2775 0.01510 0.00742 -0.0784 0.8594 0.0680
-0.750 0.3054 0.01464 0.00677 -0.0775 0.8388 0.0652
-0.500 0.3325 0.01425 0.00627 -0.0767 0.8167 0.0643
-0.250 0.3590 0.01358 0.00552 -0.0760 0.7958 0.0651
0.000 0.3855 0.01310 0.00498 -0.0754 0.7759 0.0665
0.250 0.4124 0.01283 0.00463 -0.0749 0.7563 0.0666
0.500 0.4395 0.01265 0.00435 -0.0745 0.7380 0.0673
0.750 0.4667 0.01257 0.00414 -0.0742 0.7205 0.0689
1.000 0.4942 0.01255 0.00399 -0.0739 0.7037 0.0719
1.250 0.5217 0.01258 0.00389 -0.0736 0.6872 0.0767
1.500 0.5483 0.01180 0.00390 -0.0738 0.6709 0.3839
1.750 0.5710 0.01034 0.00384 -0.0719 0.6549 1.0000
2.000 0.5982 0.01050 0.00384 -0.0716 0.6378 1.0000
2.250 0.6254 0.01067 0.00386 -0.0714 0.6209 1.0000
2.500 0.6525 0.01084 0.00390 -0.0712 0.6039 1.0000
2.750 0.6795 0.01102 0.00395 -0.0710 0.5867 1.0000
3.000 0.7063 0.01122 0.00403 -0.0707 0.5694 1.0000
3.250 0.7331 0.01145 0.00413 -0.0705 0.5525 1.0000
3.500 0.7599 0.01169 0.00427 -0.0703 0.5359 1.0000
3.750 0.7867 0.01194 0.00445 -0.0701 0.5190 1.0000
4.000 0.8134 0.01220 0.00463 -0.0700 0.5023 1.0000
4.250 0.8400 0.01248 0.00484 -0.0698 0.4862 1.0000
4.500 0.8665 0.01277 0.00506 -0.0696 0.4711 1.0000
4.750 0.8931 0.01308 0.00533 -0.0695 0.4571 1.0000
5.000 0.9195 0.01341 0.00560 -0.0693 0.4440 1.0000
5.250 0.9458 0.01375 0.00587 -0.0691 0.4308 1.0000
5.500 0.9720 0.01406 0.00617 -0.0689 0.4174 1.0000
5.750 0.9979 0.01436 0.00647 -0.0687 0.4037 1.0000
6.000 1.0238 0.01467 0.00679 -0.0685 0.3907 1.0000
6.250 1.0497 0.01501 0.00713 -0.0683 0.3790 1.0000
6.500 1.0751 0.01535 0.00748 -0.0680 0.3668 1.0000
6.750 1.1003 0.01570 0.00782 -0.0677 0.3548 1.0000
7.000 1.1255 0.01605 0.00818 -0.0674 0.3436 1.0000
7.250 1.1507 0.01637 0.00862 -0.0671 0.3327 1.0000
7.500 1.1755 0.01673 0.00902 -0.0667 0.3215 1.0000
7.750 1.1995 0.01706 0.00939 -0.0662 0.3085 1.0000
8.000 1.2229 0.01737 0.00976 -0.0657 0.2937 1.0000
8.250 1.2461 0.01770 0.01016 -0.0651 0.2783 1.0000
8.500 1.2691 0.01805 0.01059 -0.0645 0.2628 1.0000
8.750 1.2912 0.01844 0.01102 -0.0638 0.2443 1.0000
9.000 1.3125 0.01890 0.01150 -0.0629 0.2224 1.0000
9.250 1.3329 0.01947 0.01209 -0.0620 0.1990 1.0000
9.500 1.3515 0.02021 0.01277 -0.0609 0.1683 1.0000
9.750 1.3661 0.02132 0.01368 -0.0593 0.1329 1.0000
10.000 1.3775 0.02270 0.01488 -0.0573 0.1042 1.0000
10.250 1.3857 0.02433 0.01633 -0.0548 0.0690 1.0000
10.500 1.3871 0.02633 0.01817 -0.0514 0.0464 1.0000
10.750 1.3911 0.02786 0.01974 -0.0481 0.0387 1.0000
11.000 1.3920 0.02938 0.02136 -0.0445 0.0351 1.0000
11.250 1.3947 0.03093 0.02301 -0.0416 0.0323 1.0000
11.500 1.3923 0.03295 0.02511 -0.0386 0.0303 1.0000
11.750 1.3884 0.03529 0.02756 -0.0359 0.0292 1.0000
12.000 1.3880 0.03754 0.02997 -0.0340 0.0283 1.0000
12.250 1.3865 0.04008 0.03266 -0.0325 0.0275 1.0000
12.500 1.3846 0.04286 0.03558 -0.0314 0.0267 1.0000
12.750 1.3823 0.04584 0.03869 -0.0306 0.0261 1.0000
13.000 1.3800 0.04896 0.04192 -0.0301 0.0255 1.0000
13.250 1.3775 0.05217 0.04523 -0.0297 0.0250 1.0000
13.500 1.3746 0.05547 0.04861 -0.0293 0.0244 1.0000
13.750 1.3714 0.05876 0.05196 -0.0285 0.0237 1.0000
14.000 1.3702 0.06188 0.05516 -0.0273 0.0231 1.0000
14.250 1.3700 0.06508 0.05854 -0.0273 0.0227 1.0000
14.500 1.3690 0.06839 0.06202 -0.0273 0.0223 1.0000
14.750 1.3678 0.07180 0.06561 -0.0271 0.0220 1.0000
15.000 1.3653 0.07546 0.06945 -0.0272 0.0218 1.0000
15.250 1.3613 0.07943 0.07361 -0.0275 0.0216 1.0000
15.500 1.3555 0.08376 0.07814 -0.0282 0.0215 1.0000
15.750 1.3479 0.08849 0.08308 -0.0293 0.0214 1.0000
16.000 1.3381 0.09371 0.08850 -0.0309 0.0214 1.0000
16.250 1.3263 0.09942 0.09443 -0.0330 0.0214 1.0000
16.500 1.3127 0.10565 0.10089 -0.0357 0.0214 1.0000
16.750 1.2976 0.11245 0.10790 -0.0390 0.0215 1.0000
17.000 1.2810 0.11981 0.11547 -0.0430 0.0216 1.0000
17.250 1.2632 0.12775 0.12361 -0.0476 0.0218 1.0000
17.500 1.2442 0.13636 0.13242 -0.0529 0.0219 1.0000
17.750 1.2240 0.14574 0.14199 -0.0589 0.0221 1.0000
18.000 1.2027 0.15593 0.15235 -0.0657 0.0224 1.0000
18.250 1.1794 0.16733 0.16389 -0.0733 0.0227 1.0000
18.500 1.1553 0.17965 0.17630 -0.0812 0.0232 1.0000
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Polar data table (+)
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