GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il) Reynolds number: 200,000 Max Cl/Cd: 74.69 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe133-il-200000-n5.txt Download as CSV file: xf-goe133-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 133 (MVA H.11) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3437 0.08654 0.08322 -0.0248 1.0000 0.0178
-7.250 -0.3467 0.08406 0.08079 -0.0244 1.0000 0.0174
-7.000 -0.3491 0.08139 0.07818 -0.0247 1.0000 0.0169
-6.750 -0.3516 0.07864 0.07548 -0.0251 1.0000 0.0166
-6.500 -0.3263 0.07327 0.07009 -0.0335 0.9948 0.0171
-6.250 -0.2943 0.06710 0.06386 -0.0436 0.9879 0.0176
-6.000 -0.2618 0.06113 0.05780 -0.0527 0.9812 0.0174
-5.750 -0.2253 0.05477 0.05130 -0.0621 0.9762 0.0171
-5.500 -0.1919 0.04854 0.04489 -0.0695 0.9689 0.0170
-5.250 -0.1539 0.04171 0.03778 -0.0770 0.9639 0.0172
-5.000 -0.1187 0.03316 0.02870 -0.0828 0.9560 0.0184
-4.750 -0.0831 0.02723 0.02225 -0.0866 0.9512 0.0198
-4.500 -0.0541 0.02379 0.01838 -0.0877 0.9428 0.0210
-4.250 -0.0204 0.01918 0.01291 -0.0893 0.9372 0.0240
-4.000 0.0086 0.01794 0.01140 -0.0896 0.9282 0.0266
-3.750 0.0404 0.01702 0.01026 -0.0903 0.9210 0.0293
-3.500 0.0690 0.01591 0.00882 -0.0902 0.9105 0.0335
-3.250 0.0979 0.01562 0.00848 -0.0902 0.8997 0.0368
-3.000 0.1274 0.01506 0.00767 -0.0902 0.8885 0.0414
-2.750 0.1557 0.01438 0.00693 -0.0901 0.8765 0.0452
-2.500 0.1839 0.01401 0.00645 -0.0899 0.8627 0.0495
-2.250 0.2117 0.01356 0.00584 -0.0895 0.8470 0.0527
-2.000 0.2390 0.01294 0.00513 -0.0892 0.8295 0.0560
-1.750 0.2663 0.01251 0.00463 -0.0888 0.8108 0.0591
-1.500 0.2935 0.01217 0.00419 -0.0883 0.7916 0.0616
-1.250 0.3205 0.01190 0.00380 -0.0878 0.7713 0.0644
-1.000 0.3475 0.01173 0.00349 -0.0873 0.7500 0.0675
-0.750 0.3742 0.01152 0.00320 -0.0869 0.7286 0.0724
-0.500 0.4009 0.01143 0.00300 -0.0865 0.7055 0.0770
-0.250 0.4275 0.01140 0.00282 -0.0860 0.6806 0.0827
0.000 0.4538 0.01137 0.00270 -0.0855 0.6526 0.0935
0.500 0.5062 0.01116 0.00259 -0.0848 0.5975 0.2161
1.000 0.5555 0.00963 0.00262 -0.0831 0.5585 1.0000
1.250 0.5821 0.00984 0.00264 -0.0828 0.5412 1.0000
1.500 0.6087 0.01005 0.00268 -0.0825 0.5249 1.0000
1.750 0.6353 0.01026 0.00276 -0.0822 0.5101 1.0000
2.000 0.6622 0.01045 0.00284 -0.0819 0.4982 1.0000
2.250 0.6889 0.01066 0.00294 -0.0817 0.4872 1.0000
2.500 0.7159 0.01084 0.00306 -0.0815 0.4760 1.0000
2.750 0.7428 0.01103 0.00319 -0.0813 0.4656 1.0000
3.000 0.7695 0.01123 0.00333 -0.0810 0.4558 1.0000
3.250 0.7963 0.01142 0.00350 -0.0808 0.4453 1.0000
3.500 0.8230 0.01162 0.00367 -0.0806 0.4349 1.0000
3.750 0.8496 0.01183 0.00385 -0.0803 0.4241 1.0000
4.000 0.8759 0.01205 0.00405 -0.0801 0.4125 1.0000
4.250 0.9021 0.01227 0.00425 -0.0798 0.3980 1.0000
4.500 0.9280 0.01251 0.00446 -0.0795 0.3799 1.0000
4.750 0.9535 0.01278 0.00469 -0.0791 0.3570 1.0000
5.000 0.9785 0.01310 0.00493 -0.0787 0.3319 1.0000
5.250 1.0031 0.01347 0.00521 -0.0782 0.3058 1.0000
5.500 1.0271 0.01391 0.00554 -0.0777 0.2803 1.0000
5.750 1.0509 0.01439 0.00593 -0.0772 0.2589 1.0000
6.000 1.0747 0.01486 0.00634 -0.0766 0.2424 1.0000
6.250 1.0987 0.01531 0.00677 -0.0761 0.2301 1.0000
6.500 1.1225 0.01577 0.00724 -0.0756 0.2201 1.0000
6.750 1.1462 0.01622 0.00770 -0.0751 0.2099 1.0000
7.000 1.1701 0.01665 0.00817 -0.0745 0.2006 1.0000
7.250 1.1933 0.01713 0.00867 -0.0739 0.1919 1.0000
7.500 1.2171 0.01754 0.00918 -0.0734 0.1831 1.0000
7.750 1.2403 0.01800 0.00971 -0.0728 0.1745 1.0000
8.000 1.2627 0.01852 0.01026 -0.0721 0.1631 1.0000
8.250 1.2854 0.01900 0.01081 -0.0715 0.1468 1.0000
8.500 1.3066 0.01962 0.01141 -0.0706 0.1169 1.0000
8.750 1.3231 0.02071 0.01230 -0.0694 0.0918 1.0000
9.000 1.3402 0.02171 0.01329 -0.0680 0.0823 1.0000
9.250 1.3551 0.02286 0.01445 -0.0665 0.0742 1.0000
9.500 1.3737 0.02359 0.01533 -0.0653 0.0677 1.0000
9.750 1.3889 0.02459 0.01638 -0.0639 0.0619 1.0000
10.000 1.4056 0.02539 0.01731 -0.0625 0.0569 1.0000
10.250 1.4215 0.02622 0.01826 -0.0611 0.0516 1.0000
10.500 1.4346 0.02719 0.01930 -0.0594 0.0467 1.0000
10.750 1.4470 0.02806 0.02027 -0.0575 0.0411 1.0000
11.000 1.4570 0.02912 0.02141 -0.0554 0.0354 1.0000
11.250 1.4647 0.03038 0.02271 -0.0533 0.0288 1.0000
11.500 1.4697 0.03189 0.02426 -0.0511 0.0229 1.0000
11.750 1.4727 0.03361 0.02607 -0.0490 0.0194 1.0000
12.000 1.4724 0.03573 0.02826 -0.0469 0.0172 1.0000
12.250 1.4721 0.03798 0.03066 -0.0452 0.0158 1.0000
12.500 1.4712 0.04045 0.03332 -0.0440 0.0148 1.0000
12.750 1.4688 0.04325 0.03627 -0.0431 0.0138 1.0000
13.000 1.4640 0.04651 0.03966 -0.0426 0.0130 1.0000
13.250 1.4563 0.05036 0.04365 -0.0426 0.0124 1.0000
13.500 1.4474 0.05460 0.04805 -0.0431 0.0119 1.0000
13.750 1.4412 0.05867 0.05230 -0.0438 0.0116 1.0000
14.000 1.4332 0.06314 0.05696 -0.0448 0.0113 1.0000
14.250 1.4239 0.06794 0.06194 -0.0461 0.0111 1.0000
14.500 1.4136 0.07300 0.06717 -0.0476 0.0109 1.0000
14.750 1.4025 0.07830 0.07263 -0.0493 0.0107 1.0000
15.000 1.3908 0.08383 0.07832 -0.0511 0.0105 1.0000
15.250 1.3787 0.08952 0.08416 -0.0532 0.0103 1.0000
15.500 1.3664 0.09537 0.09017 -0.0554 0.0102 1.0000
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Polar data table (+)
Polar graphs
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