GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il) Reynolds number: 200,000 Max Cl/Cd: 78.03 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe144-il-200000-n5.txt Download as CSV file: xf-goe144-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 144 (MVA H.21) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3369 0.09082 0.08748 -0.0261 1.0000 0.0160
-7.750 -0.3427 0.08816 0.08489 -0.0253 1.0000 0.0159
-7.500 -0.3529 0.08590 0.08271 -0.0236 1.0000 0.0157
-7.250 -0.3641 0.08385 0.08074 -0.0217 1.0000 0.0157
-7.000 -0.3610 0.07984 0.07677 -0.0245 0.9981 0.0156
-6.750 -0.3387 0.07419 0.07110 -0.0327 0.9924 0.0158
-6.500 -0.3136 0.06831 0.06519 -0.0414 0.9868 0.0162
-6.250 -0.2878 0.06291 0.05974 -0.0494 0.9801 0.0177
-5.750 -0.2140 0.02530 0.02057 -0.0884 0.9653 0.0201
-5.500 -0.1865 0.02130 0.01583 -0.0902 0.9590 0.0216
-5.250 -0.1538 0.01975 0.01408 -0.0921 0.9549 0.0248
-5.000 -0.1228 0.01821 0.01217 -0.0931 0.9497 0.0279
-4.750 -0.0912 0.01699 0.01053 -0.0940 0.9442 0.0310
-4.500 -0.0563 0.01564 0.00896 -0.0956 0.9402 0.0350
-4.250 -0.0254 0.01496 0.00811 -0.0962 0.9335 0.0387
-4.000 0.0096 0.01424 0.00718 -0.0976 0.9278 0.0420
-3.750 0.0444 0.01364 0.00651 -0.0989 0.9218 0.0463
-3.500 0.0777 0.01319 0.00597 -0.0998 0.9139 0.0506
-3.250 0.1124 0.01276 0.00548 -0.1010 0.9061 0.0563
-3.000 0.1469 0.01240 0.00500 -0.1021 0.8970 0.0661
-2.750 0.1783 0.01215 0.00460 -0.1025 0.8852 0.0759
-2.500 0.2088 0.01184 0.00426 -0.1029 0.8718 0.0840
-2.250 0.2385 0.01162 0.00395 -0.1030 0.8558 0.0914
-2.000 0.2669 0.01147 0.00378 -0.1029 0.8353 0.1000
-1.750 0.2959 0.01136 0.00362 -0.1028 0.8084 0.1075
-1.500 0.3260 0.01124 0.00334 -0.1029 0.7763 0.1135
-1.250 0.3550 0.01122 0.00315 -0.1028 0.7466 0.1201
-1.000 0.3823 0.01127 0.00303 -0.1023 0.7222 0.1294
-0.750 0.4088 0.01134 0.00294 -0.1018 0.7014 0.1382
-0.500 0.4349 0.01136 0.00287 -0.1013 0.6833 0.1454
-0.250 0.4610 0.01142 0.00280 -0.1007 0.6669 0.1537
0.000 0.4868 0.01144 0.00277 -0.1002 0.6513 0.1611
0.250 0.5126 0.01151 0.00273 -0.0996 0.6358 0.1685
0.500 0.5379 0.01155 0.00273 -0.0990 0.6189 0.1754
0.750 0.5631 0.01162 0.00272 -0.0983 0.6002 0.1829
1.000 0.5883 0.01168 0.00275 -0.0977 0.5832 0.1897
1.250 0.6138 0.01176 0.00278 -0.0971 0.5696 0.1977
1.500 0.6394 0.01182 0.00286 -0.0966 0.5587 0.2090
1.750 0.6651 0.01189 0.00295 -0.0961 0.5477 0.2246
2.250 0.7164 0.01201 0.00316 -0.0951 0.5262 0.2675
2.750 0.7774 0.01089 0.00341 -0.0963 0.5011 1.0000
3.000 0.8023 0.01108 0.00353 -0.0956 0.4871 1.0000
3.250 0.8272 0.01127 0.00366 -0.0949 0.4731 1.0000
3.500 0.8521 0.01146 0.00381 -0.0943 0.4596 1.0000
3.750 0.8771 0.01166 0.00398 -0.0936 0.4472 1.0000
4.000 0.9018 0.01187 0.00417 -0.0930 0.4336 1.0000
4.250 0.9264 0.01209 0.00437 -0.0923 0.4193 1.0000
4.500 0.9511 0.01231 0.00459 -0.0916 0.4068 1.0000
4.750 0.9755 0.01255 0.00484 -0.0909 0.3930 1.0000
5.000 0.9995 0.01281 0.00510 -0.0901 0.3769 1.0000
5.250 1.0228 0.01312 0.00536 -0.0893 0.3567 1.0000
5.500 1.0433 0.01359 0.00565 -0.0880 0.3150 1.0000
6.000 1.0824 0.01487 0.00651 -0.0853 0.2336 1.0000
6.250 1.1018 0.01558 0.00703 -0.0841 0.1961 1.0000
6.500 1.1186 0.01655 0.00767 -0.0825 0.1341 1.0000
6.750 1.1330 0.01779 0.00857 -0.0806 0.0891 1.0000
7.000 1.1452 0.01924 0.00968 -0.0784 0.0276 1.0000
7.250 1.1636 0.02005 0.01056 -0.0768 0.0215 1.0000
7.500 1.1818 0.02082 0.01147 -0.0752 0.0188 1.0000
7.750 1.1983 0.02174 0.01252 -0.0733 0.0162 1.0000
8.000 1.2126 0.02282 0.01380 -0.0712 0.0145 1.0000
8.250 1.2248 0.02401 0.01518 -0.0688 0.0137 1.0000
8.500 1.2378 0.02502 0.01634 -0.0666 0.0133 1.0000
8.750 1.2487 0.02605 0.01750 -0.0641 0.0127 1.0000
9.000 1.2564 0.02717 0.01879 -0.0612 0.0121 1.0000
9.250 1.2637 0.02832 0.02004 -0.0584 0.0111 1.0000
9.500 1.2682 0.02968 0.02151 -0.0554 0.0107 1.0000
9.750 1.2711 0.03123 0.02317 -0.0525 0.0103 1.0000
10.000 1.2735 0.03291 0.02494 -0.0498 0.0101 1.0000
10.250 1.2749 0.03480 0.02691 -0.0473 0.0098 1.0000
10.500 1.2765 0.03683 0.02903 -0.0452 0.0095 1.0000
10.750 1.2788 0.03898 0.03126 -0.0432 0.0094 1.0000
11.000 1.2812 0.04140 0.03373 -0.0415 0.0091 1.0000
11.250 1.2870 0.04389 0.03629 -0.0400 0.0090 1.0000
11.500 1.2960 0.04664 0.03912 -0.0385 0.0087 1.0000
11.750 1.2986 0.04870 0.04138 -0.0374 0.0084 1.0000
12.000 1.3012 0.05101 0.04389 -0.0365 0.0081 1.0000
12.250 1.3033 0.05362 0.04669 -0.0358 0.0078 1.0000
12.500 1.3040 0.05648 0.04980 -0.0353 0.0075 1.0000
12.750 1.3038 0.05970 0.05321 -0.0350 0.0074 1.0000
13.000 1.3016 0.06318 0.05689 -0.0349 0.0073 1.0000
13.250 1.2976 0.06701 0.06093 -0.0352 0.0072 1.0000
13.500 1.2920 0.07114 0.06526 -0.0358 0.0072 1.0000
13.750 1.2846 0.07562 0.06995 -0.0368 0.0071 1.0000
14.000 1.2755 0.08049 0.07503 -0.0382 0.0070 1.0000
14.250 1.2654 0.08567 0.08041 -0.0401 0.0070 1.0000
14.500 1.2539 0.09132 0.08627 -0.0425 0.0070 1.0000
14.750 1.2418 0.09732 0.09246 -0.0453 0.0070 1.0000
15.000 1.2288 0.10371 0.09905 -0.0485 0.0070 1.0000
15.250 1.2153 0.11056 0.10610 -0.0522 0.0070 1.0000
15.500 1.2016 0.11777 0.11349 -0.0564 0.0071 1.0000
15.750 1.1878 0.12535 0.12125 -0.0610 0.0071 1.0000
16.000 1.1734 0.13350 0.12956 -0.0660 0.0071 1.0000
16.250 1.1593 0.14204 0.13826 -0.0715 0.0072 1.0000
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Polar data table (+)
Polar graphs
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