GOE 143 (MVA H.20) AIRFOIL (goe143-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 143 (MVA H.20) AIRFOIL (goe143-il) Reynolds number: 50,000 Max Cl/Cd: 35.33 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe143-il-50000.txt Download as CSV file: xf-goe143-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4180 0.11330 0.10633 -0.0040 1.0000 0.1411
-8.500 -0.4208 0.11172 0.10484 -0.0066 1.0000 0.1462
-8.250 -0.4348 0.11204 0.10532 -0.0117 1.0000 0.1478
-8.000 -0.4054 0.10425 0.09744 -0.0072 1.0000 0.1583
-7.750 -0.4169 0.10402 0.09735 -0.0122 1.0000 0.1625
-7.500 -0.3972 0.09817 0.09149 -0.0086 1.0000 0.1722
-7.250 -0.4064 0.09800 0.09144 -0.0172 1.0000 0.1781
-7.000 -0.3874 0.09210 0.08556 -0.0110 1.0000 0.1877
-6.500 -0.3786 0.08685 0.08043 -0.0172 1.0000 0.2077
-6.250 -0.3673 0.08277 0.07641 -0.0147 1.0000 0.2183
-6.000 -0.3600 0.07973 0.07340 -0.0151 1.0000 0.2328
-5.750 -0.3534 0.07693 0.07067 -0.0158 1.0000 0.2504
-5.250 -0.3406 0.07119 0.06507 -0.0157 1.0000 0.2878
-5.000 -0.3333 0.06841 0.06235 -0.0133 1.0000 0.3097
-4.750 -0.3281 0.06573 0.05975 -0.0115 1.0000 0.3356
-4.250 -0.3230 0.06101 0.05522 -0.0038 1.0000 0.4098
-4.000 0.0140 0.03836 0.03154 -0.0159 1.0000 1.0000
-3.750 0.0270 0.03651 0.02974 -0.0172 1.0000 1.0000
-3.500 0.0399 0.03474 0.02803 -0.0184 1.0000 1.0000
-3.250 0.0058 0.03549 0.02898 -0.0088 1.0000 0.9769
-3.000 -0.0489 0.03699 0.03074 0.0041 1.0000 0.9358
-2.750 -0.1001 0.03787 0.03190 0.0149 1.0000 0.8983
-2.500 -0.1499 0.03832 0.03267 0.0249 1.0000 0.8692
-2.250 -0.2038 0.03865 0.03327 0.0359 1.0000 0.8526
-2.000 -0.2567 0.03863 0.03349 0.0461 1.0000 0.8379
-1.750 -0.0036 0.03205 0.02300 -0.0530 1.0000 0.2083
-1.500 0.0228 0.03052 0.02129 -0.0536 1.0000 0.2052
-1.250 0.0515 0.02926 0.01970 -0.0545 1.0000 0.1981
-1.000 0.0801 0.02850 0.01852 -0.0551 1.0000 0.1921
-0.750 0.1056 0.02776 0.01760 -0.0556 1.0000 0.1902
-0.500 0.1298 0.02737 0.01701 -0.0560 1.0000 0.1911
-0.250 0.1521 0.02715 0.01669 -0.0565 1.0000 0.1960
0.000 0.1892 0.02696 0.01640 -0.0594 0.9945 0.2018
0.250 0.2575 0.02647 0.01570 -0.0670 0.9744 0.2111
0.500 0.3240 0.02592 0.01524 -0.0743 0.9537 0.2402
0.750 0.3841 0.02507 0.01482 -0.0805 0.9303 0.2962
1.000 0.4388 0.02313 0.01420 -0.0838 0.9089 1.0000
1.250 0.4915 0.02329 0.01397 -0.0876 0.8839 1.0000
1.500 0.5356 0.02341 0.01391 -0.0897 0.8590 1.0000
1.750 0.5790 0.02338 0.01375 -0.0912 0.8371 1.0000
2.000 0.6107 0.02364 0.01392 -0.0910 0.8127 1.0000
2.250 0.6442 0.02375 0.01396 -0.0906 0.7918 1.0000
2.500 0.6707 0.02416 0.01431 -0.0896 0.7692 1.0000
2.750 0.6984 0.02447 0.01458 -0.0886 0.7487 1.0000
3.000 0.7263 0.02471 0.01476 -0.0873 0.7302 1.0000
3.250 0.7502 0.02529 0.01536 -0.0862 0.7094 1.0000
3.500 0.7755 0.02572 0.01577 -0.0849 0.6902 1.0000
3.750 0.8016 0.02594 0.01596 -0.0833 0.6716 1.0000
4.000 0.8252 0.02617 0.01620 -0.0813 0.6486 1.0000
4.250 0.8506 0.02593 0.01583 -0.0787 0.6253 1.0000
4.500 0.8733 0.02610 0.01598 -0.0765 0.5993 1.0000
4.750 0.8974 0.02629 0.01609 -0.0745 0.5757 1.0000
5.000 0.9215 0.02663 0.01643 -0.0728 0.5524 1.0000
5.250 0.9448 0.02713 0.01694 -0.0712 0.5281 1.0000
5.500 0.9696 0.02747 0.01716 -0.0694 0.5037 1.0000
5.750 0.9922 0.02808 0.01777 -0.0678 0.4757 1.0000
6.000 1.0147 0.02885 0.01855 -0.0661 0.4464 1.0000
6.250 1.0371 0.02981 0.01946 -0.0646 0.4166 1.0000
6.500 1.0589 0.03098 0.02063 -0.0632 0.3886 1.0000
6.750 1.0820 0.03216 0.02175 -0.0620 0.3661 1.0000
7.000 1.1033 0.03364 0.02341 -0.0610 0.3470 1.0000
7.250 1.1256 0.03523 0.02513 -0.0602 0.3330 1.0000
7.500 1.1500 0.03674 0.02669 -0.0595 0.3232 1.0000
7.750 1.1677 0.03913 0.02951 -0.0589 0.3141 1.0000
8.000 1.1888 0.04102 0.03164 -0.0582 0.3066 1.0000
8.250 1.2126 0.04155 0.03217 -0.0571 0.2940 1.0000
8.500 1.2307 0.04193 0.03272 -0.0556 0.2775 1.0000
8.750 1.2509 0.04223 0.03313 -0.0543 0.2627 1.0000
9.000 1.2692 0.04241 0.03350 -0.0528 0.2464 1.0000
9.250 1.2867 0.04248 0.03371 -0.0511 0.2288 1.0000
9.500 1.3024 0.04178 0.03292 -0.0489 0.2043 1.0000
9.750 1.3104 0.04230 0.03341 -0.0462 0.1759 1.0000
10.000 1.3127 0.04463 0.03565 -0.0432 0.1455 1.0000
10.250 1.3224 0.04720 0.03782 -0.0412 0.1241 1.0000
10.500 1.3261 0.05027 0.04119 -0.0389 0.1123 1.0000
10.750 1.3290 0.05413 0.04546 -0.0369 0.1053 1.0000
11.000 1.3355 0.05744 0.04895 -0.0352 0.0995 1.0000
11.250 1.3378 0.06133 0.05302 -0.0335 0.0958 1.0000
11.500 1.3226 0.06565 0.05780 -0.0312 0.0944 1.0000
11.750 1.3024 0.07007 0.06256 -0.0293 0.0938 1.0000
12.000 1.2788 0.07519 0.06797 -0.0287 0.0938 1.0000
12.250 1.2524 0.08123 0.07425 -0.0298 0.0944 1.0000
12.500 1.2246 0.08827 0.08148 -0.0324 0.0953 1.0000
12.750 1.1974 0.09619 0.08953 -0.0361 0.0963 1.0000
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Polar data table (+)
Polar graphs
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