GOE 180 (MVA H.26) AIRFOIL (goe180-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 180 (MVA H.26) AIRFOIL (goe180-il) Reynolds number: 200,000 Max Cl/Cd: 78.19 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe180-il-200000.txt Download as CSV file: xf-goe180-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 180 (MVA H.26) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3467 0.09601 0.09249 -0.0269 1.0000 0.0419
-8.000 -0.3581 0.09426 0.09083 -0.0289 1.0000 0.0427
-7.750 -0.3659 0.09196 0.08861 -0.0322 1.0000 0.0431
-7.500 -0.3663 0.08873 0.08543 -0.0366 1.0000 0.0433
-7.250 -0.3668 0.08418 0.08094 -0.0324 1.0000 0.0440
-7.000 -0.3621 0.08185 0.07864 -0.0287 1.0000 0.0449
-6.750 -0.3600 0.07979 0.07663 -0.0269 1.0000 0.0462
-6.500 -0.3607 0.07763 0.07451 -0.0262 1.0000 0.0477
-6.250 -0.3615 0.07519 0.07210 -0.0265 1.0000 0.0496
-6.000 -0.3478 0.07101 0.06775 -0.0386 1.0000 0.0534
-5.750 -0.3445 0.06588 0.06261 -0.0399 1.0000 0.0542
-5.500 -0.3297 0.06288 0.05967 -0.0388 0.9978 0.0554
-5.250 -0.2984 0.05965 0.05642 -0.0424 0.9941 0.0583
-5.000 -0.2413 0.05182 0.04812 -0.0577 0.9879 0.0665
-4.750 -0.2141 0.04935 0.04576 -0.0591 0.9845 0.0692
-4.500 -0.1624 0.04439 0.04018 -0.0686 0.9777 0.0798
-4.250 -0.1315 0.04074 0.03667 -0.0713 0.9738 0.0821
-4.000 -0.0821 0.04010 0.03534 -0.0762 0.9665 0.0936
-3.750 -0.0531 0.03437 0.02989 -0.0795 0.9620 0.0974
-3.500 -0.0095 0.03181 0.02685 -0.0837 0.9563 0.1102
-3.250 0.0254 0.02909 0.02420 -0.0861 0.9498 0.1139
-3.000 0.0773 0.02304 0.01711 -0.0900 0.9466 0.0823
-2.750 0.1187 0.01943 0.01271 -0.0913 0.9397 0.0641
-2.500 0.1600 0.01738 0.01036 -0.0936 0.9335 0.0628
-2.250 0.1971 0.01599 0.00876 -0.0949 0.9237 0.0627
-2.000 0.2360 0.01510 0.00769 -0.0965 0.9138 0.0646
-1.750 0.2729 0.01422 0.00668 -0.0978 0.9016 0.0655
-1.500 0.3040 0.01315 0.00560 -0.0979 0.8845 0.0671
-1.250 0.3327 0.01255 0.00501 -0.0976 0.8632 0.0698
-1.000 0.3610 0.01214 0.00453 -0.0971 0.8390 0.0737
-0.750 0.3878 0.01183 0.00412 -0.0963 0.8100 0.0794
-0.500 0.4140 0.01150 0.00372 -0.0954 0.7773 0.0939
-0.250 0.4392 0.01065 0.00341 -0.0949 0.7452 0.2693
0.000 0.4648 0.00892 0.00332 -0.0936 0.7169 1.0000
0.250 0.4908 0.00914 0.00322 -0.0930 0.6916 1.0000
0.500 0.5170 0.00936 0.00319 -0.0924 0.6691 1.0000
0.750 0.5433 0.00960 0.00320 -0.0919 0.6502 1.0000
1.000 0.5699 0.00983 0.00324 -0.0915 0.6348 1.0000
1.250 0.5967 0.01005 0.00331 -0.0912 0.6214 1.0000
1.500 0.6235 0.01028 0.00340 -0.0908 0.6092 1.0000
1.750 0.6503 0.01053 0.00349 -0.0905 0.5982 1.0000
2.000 0.6771 0.01074 0.00361 -0.0902 0.5869 1.0000
2.250 0.7038 0.01095 0.00374 -0.0899 0.5756 1.0000
2.500 0.7306 0.01118 0.00388 -0.0897 0.5655 1.0000
2.750 0.7573 0.01141 0.00403 -0.0894 0.5557 1.0000
3.000 0.7841 0.01161 0.00421 -0.0891 0.5461 1.0000
3.250 0.8109 0.01187 0.00439 -0.0889 0.5380 1.0000
3.500 0.8375 0.01206 0.00458 -0.0886 0.5283 1.0000
3.750 0.8639 0.01228 0.00478 -0.0882 0.5188 1.0000
4.000 0.8903 0.01252 0.00497 -0.0879 0.5091 1.0000
4.250 0.9163 0.01269 0.00518 -0.0875 0.4984 1.0000
4.500 0.9423 0.01290 0.00539 -0.0871 0.4881 1.0000
4.750 0.9683 0.01314 0.00557 -0.0867 0.4778 1.0000
5.000 0.9939 0.01330 0.00582 -0.0862 0.4660 1.0000
5.250 1.0194 0.01350 0.00606 -0.0857 0.4543 1.0000
5.500 1.0447 0.01370 0.00629 -0.0852 0.4419 1.0000
5.750 1.0696 0.01390 0.00653 -0.0846 0.4279 1.0000
6.000 1.0941 0.01411 0.00678 -0.0839 0.4119 1.0000
6.250 1.1182 0.01433 0.00703 -0.0832 0.3934 1.0000
6.500 1.1416 0.01461 0.00728 -0.0824 0.3732 1.0000
6.750 1.1650 0.01490 0.00762 -0.0816 0.3498 1.0000
7.000 1.1874 0.01530 0.00797 -0.0806 0.3269 1.0000
7.250 1.2086 0.01579 0.00835 -0.0796 0.3009 1.0000
7.500 1.2287 0.01640 0.00883 -0.0784 0.2745 1.0000
7.750 1.2486 0.01708 0.00944 -0.0773 0.2534 1.0000
8.000 1.2690 0.01774 0.01008 -0.0763 0.2360 1.0000
8.250 1.2893 0.01839 0.01073 -0.0752 0.2205 1.0000
8.500 1.3096 0.01899 0.01136 -0.0742 0.2046 1.0000
8.750 1.3300 0.01954 0.01196 -0.0732 0.1871 1.0000
9.000 1.3501 0.02007 0.01248 -0.0721 0.1584 1.0000
9.250 1.3595 0.02161 0.01361 -0.0698 0.0993 1.0000
9.500 1.3601 0.02395 0.01547 -0.0662 0.0505 1.0000
9.750 1.3676 0.02550 0.01709 -0.0633 0.0432 1.0000
10.000 1.3705 0.02710 0.01877 -0.0599 0.0394 1.0000
10.250 1.3708 0.02877 0.02056 -0.0563 0.0373 1.0000
10.500 1.3748 0.03028 0.02224 -0.0534 0.0357 1.0000
10.750 1.3768 0.03202 0.02409 -0.0506 0.0342 1.0000
11.000 1.3776 0.03396 0.02612 -0.0482 0.0328 1.0000
11.250 1.3761 0.03623 0.02846 -0.0459 0.0315 1.0000
11.500 1.3712 0.03906 0.03132 -0.0436 0.0303 1.0000
11.750 1.3738 0.04135 0.03371 -0.0419 0.0294 1.0000
12.000 1.3788 0.04346 0.03596 -0.0405 0.0287 1.0000
12.250 1.3839 0.04567 0.03829 -0.0391 0.0280 1.0000
12.500 1.3898 0.04791 0.04065 -0.0377 0.0273 1.0000
12.750 1.3964 0.05018 0.04302 -0.0364 0.0267 1.0000
13.000 1.4022 0.05257 0.04555 -0.0352 0.0261 1.0000
13.250 1.4065 0.05513 0.04823 -0.0342 0.0255 1.0000
13.500 1.4100 0.05779 0.05098 -0.0333 0.0248 1.0000
13.750 1.4166 0.06052 0.05376 -0.0322 0.0240 1.0000
14.000 1.4234 0.06474 0.05814 -0.0305 0.0233 1.0000
14.250 1.4168 0.06833 0.06196 -0.0302 0.0232 1.0000
14.500 1.4086 0.07228 0.06617 -0.0303 0.0231 1.0000
14.750 1.3990 0.07662 0.07074 -0.0307 0.0231 1.0000
15.000 1.3879 0.08130 0.07565 -0.0315 0.0231 1.0000
15.250 1.3748 0.08637 0.08094 -0.0327 0.0231 1.0000
15.500 1.3606 0.09182 0.08660 -0.0344 0.0231 1.0000
15.750 1.3457 0.09760 0.09259 -0.0364 0.0232 1.0000
16.000 1.3301 0.10380 0.09898 -0.0387 0.0232 1.0000
16.250 1.3158 0.10986 0.10524 -0.0416 0.0234 1.0000
16.500 1.3006 0.11615 0.11171 -0.0454 0.0234 1.0000
16.750 1.2853 0.12282 0.11858 -0.0498 0.0236 1.0000
17.000 1.2676 0.13054 0.12650 -0.0552 0.0238 1.0000
17.250 1.2441 0.14045 0.13666 -0.0627 0.0241 1.0000
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