GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.39 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe142-il-1000000-n5.txt Download as CSV file: xf-goe142-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 142 (MVA H.19) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4102 0.09184 0.09027 -0.0089 1.0000 0.0042
-7.750 -0.4071 0.08788 0.08632 -0.0111 1.0000 0.0044
-7.500 -0.4038 0.08330 0.08176 -0.0144 1.0000 0.0047
-7.250 -0.3946 0.07865 0.07712 -0.0190 1.0000 0.0049
-7.000 -0.3799 0.07375 0.07222 -0.0249 0.9969 0.0050
-6.000 -0.2629 0.01416 0.01039 -0.0784 0.9485 0.0071
-5.750 -0.2369 0.01289 0.00885 -0.0782 0.9383 0.0073
-5.500 -0.2109 0.01200 0.00772 -0.0779 0.9271 0.0074
-5.250 -0.1845 0.01138 0.00692 -0.0775 0.9149 0.0076
-5.000 -0.1582 0.01026 0.00554 -0.0773 0.9025 0.0081
-4.750 -0.1315 0.00982 0.00498 -0.0770 0.8894 0.0085
-4.500 -0.1045 0.00953 0.00459 -0.0767 0.8754 0.0090
-4.250 -0.0774 0.00929 0.00425 -0.0764 0.8605 0.0096
-4.000 -0.0503 0.00902 0.00384 -0.0761 0.8439 0.0102
-3.750 -0.0230 0.00875 0.00344 -0.0758 0.8262 0.0107
-3.500 0.0044 0.00853 0.00310 -0.0756 0.8073 0.0110
-3.250 0.0318 0.00816 0.00259 -0.0754 0.7885 0.0119
-3.000 0.0594 0.00800 0.00233 -0.0752 0.7691 0.0128
-2.750 0.0870 0.00788 0.00211 -0.0751 0.7486 0.0139
-2.500 0.1146 0.00780 0.00193 -0.0749 0.7276 0.0151
-2.250 0.1423 0.00768 0.00171 -0.0748 0.7055 0.0168
-2.000 0.1700 0.00762 0.00156 -0.0747 0.6817 0.0190
-1.750 0.1977 0.00760 0.00143 -0.0745 0.6576 0.0210
-1.500 0.2254 0.00758 0.00130 -0.0744 0.6333 0.0230
-1.250 0.2532 0.00756 0.00121 -0.0744 0.6094 0.0272
-1.000 0.2809 0.00759 0.00114 -0.0743 0.5860 0.0303
-0.750 0.3088 0.00759 0.00107 -0.0742 0.5630 0.0351
-0.500 0.3365 0.00761 0.00103 -0.0742 0.5410 0.0404
-0.250 0.3643 0.00765 0.00099 -0.0741 0.5191 0.0454
0.000 0.3922 0.00769 0.00097 -0.0741 0.4995 0.0526
0.250 0.4199 0.00773 0.00096 -0.0740 0.4783 0.0618
0.500 0.4477 0.00780 0.00096 -0.0740 0.4594 0.0701
0.750 0.4754 0.00785 0.00098 -0.0740 0.4402 0.0829
1.000 0.5031 0.00791 0.00100 -0.0739 0.4214 0.0985
1.250 0.5308 0.00797 0.00104 -0.0739 0.4029 0.1202
1.500 0.5585 0.00799 0.00110 -0.0739 0.3858 0.1635
1.750 0.5845 0.00681 0.00129 -0.0744 0.3695 0.7537
2.250 0.6364 0.00653 0.00139 -0.0732 0.3404 1.0000
2.500 0.6639 0.00669 0.00147 -0.0732 0.3252 1.0000
2.750 0.6915 0.00684 0.00155 -0.0731 0.3127 1.0000
3.000 0.7190 0.00699 0.00164 -0.0730 0.3005 1.0000
3.250 0.7464 0.00716 0.00174 -0.0730 0.2870 1.0000
3.500 0.7737 0.00733 0.00184 -0.0729 0.2750 1.0000
3.750 0.8011 0.00749 0.00197 -0.0728 0.2639 1.0000
4.000 0.8284 0.00767 0.00209 -0.0727 0.2519 1.0000
4.250 0.8556 0.00784 0.00223 -0.0726 0.2411 1.0000
4.500 0.8827 0.00802 0.00237 -0.0725 0.2314 1.0000
4.750 0.9097 0.00823 0.00254 -0.0724 0.2200 1.0000
5.000 0.9368 0.00841 0.00270 -0.0723 0.2106 1.0000
5.250 0.9633 0.00867 0.00289 -0.0722 0.1950 1.0000
5.500 0.9895 0.00899 0.00311 -0.0720 0.1744 1.0000
5.750 1.0158 0.00926 0.00334 -0.0718 0.1596 1.0000
6.000 1.0415 0.00963 0.00360 -0.0716 0.1397 1.0000
6.250 1.0673 0.00997 0.00387 -0.0714 0.1228 1.0000
6.500 1.0929 0.01033 0.00417 -0.0711 0.1066 1.0000
6.750 1.1176 0.01084 0.00456 -0.0708 0.0829 1.0000
7.000 1.1409 0.01154 0.00507 -0.0703 0.0529 1.0000
7.250 1.1648 0.01214 0.00558 -0.0698 0.0336 1.0000
7.500 1.1891 0.01266 0.00604 -0.0694 0.0228 1.0000
7.750 1.2139 0.01307 0.00644 -0.0690 0.0185 1.0000
8.000 1.2385 0.01350 0.00689 -0.0687 0.0149 1.0000
8.250 1.2632 0.01389 0.00731 -0.0683 0.0130 1.0000
8.500 1.2872 0.01437 0.00781 -0.0678 0.0109 1.0000
8.750 1.3113 0.01481 0.00829 -0.0674 0.0096 1.0000
9.000 1.3352 0.01526 0.00877 -0.0669 0.0087 1.0000
9.250 1.3584 0.01578 0.00933 -0.0664 0.0076 1.0000
9.500 1.3807 0.01642 0.01002 -0.0657 0.0065 1.0000
9.750 1.4037 0.01691 0.01057 -0.0651 0.0063 1.0000
10.000 1.4262 0.01744 0.01116 -0.0645 0.0058 1.0000
10.250 1.4483 0.01800 0.01178 -0.0638 0.0054 1.0000
10.500 1.4696 0.01860 0.01243 -0.0631 0.0049 1.0000
10.750 1.4900 0.01930 0.01320 -0.0622 0.0045 1.0000
11.000 1.5083 0.02020 0.01419 -0.0610 0.0041 1.0000
11.250 1.5275 0.02093 0.01500 -0.0600 0.0040 1.0000
11.500 1.5462 0.02166 0.01582 -0.0590 0.0039 1.0000
11.750 1.5639 0.02244 0.01669 -0.0578 0.0037 1.0000
12.000 1.5804 0.02327 0.01761 -0.0565 0.0035 1.0000
12.250 1.5956 0.02416 0.01859 -0.0550 0.0034 1.0000
12.500 1.6094 0.02510 0.01962 -0.0534 0.0032 1.0000
12.750 1.6206 0.02606 0.02069 -0.0514 0.0031 1.0000
13.000 1.6281 0.02710 0.02182 -0.0489 0.0030 1.0000
13.250 1.6340 0.02829 0.02310 -0.0465 0.0029 1.0000
13.500 1.6383 0.02968 0.02459 -0.0442 0.0028 1.0000
13.750 1.6405 0.03135 0.02637 -0.0421 0.0027 1.0000
14.000 1.6402 0.03341 0.02855 -0.0403 0.0026 1.0000
14.250 1.6360 0.03604 0.03133 -0.0388 0.0025 1.0000
14.500 1.6297 0.03919 0.03463 -0.0380 0.0024 1.0000
14.750 1.6211 0.04298 0.03857 -0.0379 0.0023 1.0000
15.000 1.6165 0.04657 0.04231 -0.0383 0.0023 1.0000
15.250 1.6091 0.05084 0.04672 -0.0394 0.0023 1.0000
15.500 1.6003 0.05556 0.05158 -0.0409 0.0023 1.0000
15.750 1.5880 0.06108 0.05725 -0.0430 0.0023 1.0000
16.000 1.5725 0.06729 0.06361 -0.0455 0.0023 1.0000
16.250 1.5534 0.07428 0.07075 -0.0485 0.0023 1.0000
16.500 1.5320 0.08180 0.07842 -0.0517 0.0023 1.0000
16.750 1.5088 0.08975 0.08651 -0.0551 0.0023 1.0000
17.000 1.4841 0.09815 0.09505 -0.0588 0.0023 1.0000
17.250 1.4605 0.10644 0.10346 -0.0624 0.0023 1.0000
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Polar data table (+)
Polar graphs
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