GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il) Reynolds number: 100,000 Max Cl/Cd: 55.73 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe142-il-100000.txt Download as CSV file: xf-goe142-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4035 0.11082 0.10589 -0.0099 1.0000 0.0535
-8.250 -0.4034 0.10963 0.10477 -0.0136 1.0000 0.0540
-8.000 -0.4019 0.10813 0.10335 -0.0182 1.0000 0.0543
-7.750 -0.3934 0.10585 0.10110 -0.0245 1.0000 0.0545
-7.500 -0.3868 0.09924 0.09455 -0.0215 1.0000 0.0553
-7.250 -0.3768 0.09390 0.08923 -0.0166 1.0000 0.0569
-7.000 -0.3683 0.09047 0.08583 -0.0169 1.0000 0.0585
-6.750 -0.3600 0.08733 0.08272 -0.0184 1.0000 0.0604
-6.500 -0.3513 0.08425 0.07968 -0.0207 1.0000 0.0625
-6.250 -0.3412 0.08127 0.07672 -0.0240 1.0000 0.0650
-6.000 -0.3204 0.07974 0.07511 -0.0351 1.0000 0.0679
-5.750 -0.3074 0.07592 0.07127 -0.0390 1.0000 0.0688
-5.500 -0.3091 0.07138 0.06689 -0.0325 1.0000 0.0710
-5.250 -0.3011 0.06849 0.06404 -0.0314 1.0000 0.0742
-5.000 -0.2875 0.06561 0.06114 -0.0334 1.0000 0.0784
-4.750 -0.2544 0.06316 0.05837 -0.0430 1.0000 0.0830
-4.500 -0.2521 0.05897 0.05435 -0.0396 1.0000 0.0847
-4.250 -0.2426 0.05613 0.05155 -0.0383 1.0000 0.0878
-3.750 -0.1998 0.05014 0.04529 -0.0430 1.0000 0.0991
-3.500 -0.1861 0.04753 0.04266 -0.0423 1.0000 0.1039
-3.250 -0.1594 0.04476 0.03965 -0.0451 1.0000 0.1132
-3.000 -0.1363 0.04262 0.03732 -0.0464 1.0000 0.1264
-2.750 -0.1163 0.04029 0.03490 -0.0470 1.0000 0.1406
-2.500 -0.0950 0.03797 0.03249 -0.0476 1.0000 0.1550
-2.250 -0.0741 0.03564 0.03012 -0.0480 1.0000 0.1705
-2.000 -0.0504 0.03389 0.02821 -0.0489 1.0000 0.1974
-1.250 0.1019 0.02429 0.01639 -0.0592 0.9913 0.0953
-1.000 0.1542 0.02224 0.01406 -0.0640 0.9845 0.1026
-0.750 0.2044 0.02065 0.01205 -0.0678 0.9752 0.1070
-0.500 0.2542 0.01950 0.01074 -0.0718 0.9654 0.1226
-0.250 0.3062 0.01829 0.00952 -0.0762 0.9566 0.1413
0.000 0.3518 0.01729 0.00864 -0.0794 0.9445 0.1687
0.250 0.3983 0.01625 0.00788 -0.0827 0.9325 0.2325
0.500 0.4396 0.01398 0.00720 -0.0841 0.9207 1.0000
0.750 0.4799 0.01382 0.00682 -0.0857 0.9045 1.0000
1.000 0.5164 0.01363 0.00648 -0.0864 0.8873 1.0000
1.250 0.5471 0.01349 0.00623 -0.0860 0.8674 1.0000
1.500 0.5756 0.01336 0.00600 -0.0850 0.8462 1.0000
1.750 0.6021 0.01328 0.00582 -0.0837 0.8234 1.0000
2.000 0.6284 0.01321 0.00563 -0.0822 0.8007 1.0000
2.250 0.6531 0.01324 0.00555 -0.0807 0.7745 1.0000
2.500 0.6779 0.01332 0.00551 -0.0793 0.7476 1.0000
2.750 0.7028 0.01345 0.00553 -0.0779 0.7199 1.0000
3.000 0.7276 0.01363 0.00558 -0.0766 0.6917 1.0000
3.250 0.7524 0.01387 0.00567 -0.0755 0.6629 1.0000
3.500 0.7772 0.01416 0.00582 -0.0744 0.6343 1.0000
3.750 0.8019 0.01449 0.00605 -0.0733 0.6059 1.0000
4.000 0.8267 0.01487 0.00630 -0.0724 0.5780 1.0000
4.250 0.8515 0.01528 0.00660 -0.0715 0.5509 1.0000
4.500 0.8762 0.01573 0.00694 -0.0707 0.5252 1.0000
4.750 0.9010 0.01622 0.00735 -0.0699 0.5011 1.0000
5.000 0.9257 0.01672 0.00780 -0.0692 0.4770 1.0000
5.250 0.9505 0.01727 0.00830 -0.0686 0.4545 1.0000
5.500 0.9752 0.01784 0.00880 -0.0679 0.4336 1.0000
5.750 0.9998 0.01844 0.00939 -0.0673 0.4134 1.0000
6.000 1.0244 0.01905 0.01006 -0.0666 0.3940 1.0000
6.250 1.0491 0.01971 0.01068 -0.0660 0.3764 1.0000
6.500 1.0735 0.02039 0.01139 -0.0654 0.3591 1.0000
6.750 1.0974 0.02106 0.01217 -0.0647 0.3415 1.0000
7.000 1.1211 0.02172 0.01295 -0.0640 0.3242 1.0000
7.250 1.1442 0.02230 0.01352 -0.0632 0.3060 1.0000
7.500 1.1654 0.02274 0.01409 -0.0622 0.2846 1.0000
7.750 1.1858 0.02308 0.01439 -0.0611 0.2623 1.0000
8.000 1.2054 0.02345 0.01497 -0.0599 0.2385 1.0000
8.250 1.2240 0.02388 0.01559 -0.0586 0.2123 1.0000
8.500 1.2396 0.02444 0.01624 -0.0570 0.1712 1.0000
8.750 1.2471 0.02656 0.01792 -0.0546 0.1069 1.0000
9.000 1.2563 0.02891 0.02007 -0.0522 0.0813 1.0000
9.250 1.2672 0.03116 0.02231 -0.0499 0.0699 1.0000
9.500 1.2786 0.03347 0.02457 -0.0479 0.0617 1.0000
9.750 1.2932 0.03556 0.02679 -0.0462 0.0558 1.0000
10.000 1.3110 0.03904 0.03017 -0.0450 0.0519 1.0000
10.250 1.3260 0.04142 0.03301 -0.0432 0.0491 1.0000
10.500 1.3379 0.04387 0.03574 -0.0415 0.0457 1.0000
10.750 1.3496 0.04677 0.03883 -0.0399 0.0435 1.0000
11.000 1.3600 0.05065 0.04294 -0.0385 0.0423 1.0000
11.250 1.3638 0.05513 0.04776 -0.0366 0.0417 1.0000
11.500 1.3607 0.05944 0.05245 -0.0344 0.0415 1.0000
11.750 1.3516 0.06325 0.05661 -0.0317 0.0416 1.0000
12.000 1.3374 0.06666 0.06033 -0.0289 0.0417 1.0000
12.250 1.3202 0.07018 0.06415 -0.0270 0.0419 1.0000
12.500 1.3000 0.07421 0.06847 -0.0262 0.0421 1.0000
12.750 1.2769 0.07909 0.07366 -0.0270 0.0425 1.0000
13.000 1.2493 0.08530 0.08016 -0.0297 0.0431 1.0000
13.250 1.2124 0.09397 0.08915 -0.0357 0.0440 1.0000
13.500 1.1656 0.10668 0.10214 -0.0457 0.0455 1.0000
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Polar data table (+)
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