GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il) Reynolds number: 500,000 Max Cl/Cd: 94.75 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe142-il-500000-n5.txt Download as CSV file: xf-goe142-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4029 0.09333 0.09110 -0.0097 1.0000 0.0073
-7.750 -0.3989 0.08958 0.08738 -0.0119 1.0000 0.0074
-7.500 -0.3947 0.08586 0.08370 -0.0145 1.0000 0.0076
-7.250 -0.3872 0.08188 0.07974 -0.0179 1.0000 0.0076
-7.000 -0.3781 0.07806 0.07593 -0.0214 1.0000 0.0077
-6.750 -0.3676 0.07572 0.07362 -0.0230 1.0000 0.0080
-6.500 -0.3578 0.07344 0.07135 -0.0244 1.0000 0.0083
-6.250 -0.3358 0.06992 0.06782 -0.0295 0.9965 0.0091
-6.000 -0.3051 0.06474 0.06260 -0.0377 0.9904 0.0097
-5.750 -0.2721 0.05912 0.05691 -0.0462 0.9841 0.0093
-5.500 -0.2387 0.05321 0.05088 -0.0542 0.9757 0.0089
-5.250 -0.2022 0.04693 0.04446 -0.0621 0.9681 0.0088
-5.000 -0.1669 0.04092 0.03826 -0.0682 0.9588 0.0090
-4.750 -0.1323 0.03454 0.03160 -0.0732 0.9489 0.0096
-4.500 -0.0947 0.01441 0.00955 -0.0795 0.9410 0.0113
-4.250 -0.0673 0.01325 0.00815 -0.0795 0.9302 0.0119
-4.000 -0.0402 0.01251 0.00722 -0.0792 0.9189 0.0125
-3.750 -0.0132 0.01178 0.00630 -0.0789 0.9067 0.0133
-3.500 0.0136 0.01110 0.00543 -0.0785 0.8936 0.0142
-3.250 0.0403 0.01053 0.00468 -0.0780 0.8791 0.0150
-3.000 0.0670 0.01004 0.00403 -0.0775 0.8636 0.0160
-2.750 0.0938 0.00972 0.00363 -0.0772 0.8471 0.0178
-2.500 0.1207 0.00946 0.00326 -0.0767 0.8299 0.0193
-2.250 0.1478 0.00921 0.00288 -0.0764 0.8119 0.0210
-2.000 0.1749 0.00893 0.00247 -0.0760 0.7928 0.0230
-1.750 0.2020 0.00881 0.00227 -0.0757 0.7726 0.0265
-1.500 0.2292 0.00874 0.00210 -0.0754 0.7507 0.0297
-1.250 0.2564 0.00860 0.00185 -0.0751 0.7282 0.0335
-1.000 0.2836 0.00857 0.00172 -0.0749 0.7041 0.0388
-0.750 0.3109 0.00856 0.00159 -0.0746 0.6796 0.0427
-0.500 0.3382 0.00853 0.00148 -0.0744 0.6554 0.0498
-0.250 0.3654 0.00856 0.00140 -0.0742 0.6308 0.0574
0.000 0.3928 0.00859 0.00135 -0.0741 0.6063 0.0665
0.250 0.4201 0.00862 0.00132 -0.0739 0.5827 0.0784
0.750 0.4748 0.00872 0.00130 -0.0737 0.5364 0.1115
1.000 0.5021 0.00874 0.00133 -0.0736 0.5141 0.1487
1.250 0.5293 0.00844 0.00141 -0.0738 0.4926 0.3358
1.750 0.5791 0.00722 0.00153 -0.0726 0.4519 1.0000
2.250 0.6335 0.00759 0.00166 -0.0723 0.4126 1.0000
2.500 0.6607 0.00778 0.00174 -0.0722 0.3939 1.0000
2.750 0.6878 0.00797 0.00185 -0.0720 0.3771 1.0000
3.250 0.7419 0.00836 0.00208 -0.0718 0.3444 1.0000
3.500 0.7690 0.00856 0.00221 -0.0716 0.3302 1.0000
3.750 0.7960 0.00876 0.00236 -0.0715 0.3159 1.0000
4.000 0.8228 0.00898 0.00252 -0.0714 0.3014 1.0000
4.250 0.8497 0.00919 0.00269 -0.0712 0.2888 1.0000
4.500 0.8764 0.00942 0.00287 -0.0711 0.2760 1.0000
5.000 0.9297 0.00987 0.00328 -0.0707 0.2513 1.0000
5.250 0.9562 0.01012 0.00350 -0.0705 0.2394 1.0000
5.500 0.9826 0.01037 0.00374 -0.0704 0.2283 1.0000
5.750 1.0086 0.01066 0.00401 -0.0701 0.2136 1.0000
6.000 1.0340 0.01105 0.00430 -0.0699 0.1919 1.0000
6.250 1.0596 0.01141 0.00459 -0.0696 0.1734 1.0000
6.500 1.0848 0.01179 0.00492 -0.0693 0.1556 1.0000
6.750 1.1097 0.01222 0.00529 -0.0690 0.1366 1.0000
7.000 1.1343 0.01270 0.00569 -0.0686 0.1158 1.0000
7.250 1.1581 0.01327 0.00616 -0.0682 0.0921 1.0000
7.500 1.1802 0.01409 0.00680 -0.0676 0.0601 1.0000
7.750 1.2022 0.01491 0.00749 -0.0669 0.0375 1.0000
8.000 1.2250 0.01558 0.00815 -0.0663 0.0264 1.0000
8.250 1.2479 0.01621 0.00878 -0.0657 0.0202 1.0000
8.500 1.2705 0.01686 0.00946 -0.0650 0.0163 1.0000
8.750 1.2932 0.01746 0.01014 -0.0644 0.0143 1.0000
9.000 1.3157 0.01807 0.01083 -0.0637 0.0127 1.0000
9.250 1.3371 0.01879 0.01161 -0.0629 0.0113 1.0000
9.500 1.3565 0.01976 0.01269 -0.0619 0.0100 1.0000
9.750 1.3775 0.02044 0.01348 -0.0610 0.0094 1.0000
10.000 1.3976 0.02118 0.01431 -0.0601 0.0086 1.0000
10.250 1.4168 0.02197 0.01519 -0.0591 0.0079 1.0000
10.500 1.4344 0.02291 0.01622 -0.0579 0.0073 1.0000
10.750 1.4487 0.02413 0.01755 -0.0563 0.0068 1.0000
11.000 1.4601 0.02554 0.01910 -0.0544 0.0065 1.0000
11.250 1.4739 0.02659 0.02031 -0.0528 0.0063 1.0000
11.500 1.4857 0.02773 0.02157 -0.0510 0.0060 1.0000
11.750 1.4940 0.02888 0.02285 -0.0486 0.0057 1.0000
12.000 1.5006 0.03012 0.02420 -0.0462 0.0054 1.0000
12.250 1.5058 0.03151 0.02572 -0.0441 0.0052 1.0000
12.500 1.5104 0.03305 0.02738 -0.0421 0.0049 1.0000
12.750 1.5134 0.03485 0.02930 -0.0405 0.0048 1.0000
13.000 1.5139 0.03704 0.03162 -0.0391 0.0046 1.0000
13.250 1.5124 0.03963 0.03434 -0.0382 0.0045 1.0000
13.500 1.5081 0.04279 0.03765 -0.0378 0.0044 1.0000
13.750 1.5007 0.04664 0.04165 -0.0380 0.0043 1.0000
14.000 1.4907 0.05119 0.04636 -0.0390 0.0042 1.0000
14.250 1.4775 0.05650 0.05185 -0.0406 0.0041 1.0000
14.500 1.4642 0.06215 0.05766 -0.0426 0.0041 1.0000
14.750 1.4539 0.06753 0.06320 -0.0448 0.0040 1.0000
15.000 1.4413 0.07342 0.06927 -0.0472 0.0040 1.0000
15.250 1.4269 0.07970 0.07571 -0.0498 0.0040 1.0000
15.500 1.4122 0.08615 0.08230 -0.0525 0.0040 1.0000
15.750 1.3964 0.09296 0.08925 -0.0555 0.0040 1.0000
16.000 1.3804 0.09990 0.09632 -0.0586 0.0040 1.0000
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Polar data table (+)
Polar graphs
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