GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 380 AIRFOIL (goe380-il) Reynolds number: 200,000 Max Cl/Cd: 78.01 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe380-il-200000-n5.txt Download as CSV file: xf-goe380-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 380 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 -0.2619 0.10044 0.09720 -0.0254 1.0000 0.0136
-7.750 -0.2634 0.09889 0.09571 -0.0246 1.0000 0.0139
-7.500 -0.2680 0.09742 0.09431 -0.0231 1.0000 0.0140
-7.250 -0.2572 0.09520 0.09213 -0.0268 0.9951 0.0143
-7.000 -0.2345 0.09177 0.08870 -0.0336 0.9875 0.0145
-6.750 -0.2096 0.08822 0.08514 -0.0409 0.9797 0.0147
-6.500 -0.1856 0.08452 0.08143 -0.0468 0.9725 0.0148
-5.500 -0.0799 0.06793 0.06472 -0.0690 0.9440 0.0153
-5.250 -0.0625 0.06257 0.05933 -0.0718 0.9368 0.0160
-5.000 -0.0438 0.05913 0.05588 -0.0732 0.9284 0.0176
-4.750 -0.0171 0.05585 0.05254 -0.0770 0.9183 0.0185
-4.500 0.0126 0.05245 0.04906 -0.0813 0.9090 0.0197
-4.250 0.0436 0.04910 0.04559 -0.0853 0.8988 0.0210
-4.000 0.0737 0.04597 0.04234 -0.0885 0.8865 0.0227
-3.750 0.1153 0.04325 0.03936 -0.0930 0.8733 0.0260
-3.500 0.1498 0.04046 0.03631 -0.0955 0.8594 0.0264
-3.000 0.2065 0.03482 0.03022 -0.0974 0.8266 0.0265
-2.750 0.2278 0.03049 0.02570 -0.0972 0.8095 0.0142
-2.500 0.2542 0.02773 0.02264 -0.0973 0.7923 0.0135
-2.250 0.2816 0.02527 0.01987 -0.0970 0.7756 0.0138
-2.000 0.3093 0.02323 0.01750 -0.0964 0.7596 0.0147
-1.750 0.3361 0.02095 0.01485 -0.0956 0.7432 0.0150
-1.500 0.3622 0.01826 0.01168 -0.0946 0.7265 0.0148
-1.250 0.3885 0.01616 0.00905 -0.0936 0.7086 0.0150
-1.000 0.4146 0.01422 0.00657 -0.0926 0.6908 0.0156
-0.750 0.4399 0.01312 0.00513 -0.0917 0.6723 0.0191
-0.500 0.4649 0.01253 0.00430 -0.0908 0.6534 0.0219
-0.250 0.4898 0.01212 0.00367 -0.0899 0.6353 0.0257
0.000 0.5145 0.01188 0.00340 -0.0891 0.6185 0.0434
0.250 0.5406 0.01210 0.00350 -0.0885 0.6032 0.0722
0.500 0.5666 0.01235 0.00358 -0.0881 0.5890 0.0875
0.750 0.5918 0.01235 0.00345 -0.0875 0.5758 0.0955
1.000 0.6166 0.01229 0.00329 -0.0869 0.5634 0.1017
1.250 0.6414 0.01226 0.00317 -0.0862 0.5519 0.1077
1.500 0.6664 0.01225 0.00307 -0.0857 0.5411 0.1137
1.750 0.6915 0.01226 0.00302 -0.0852 0.5309 0.1218
2.000 0.7166 0.01230 0.00301 -0.0846 0.5207 0.1334
2.500 0.7969 0.01102 0.00324 -0.0905 0.4964 1.0000
2.750 0.8212 0.01120 0.00332 -0.0898 0.4846 1.0000
3.000 0.8452 0.01138 0.00343 -0.0891 0.4718 1.0000
3.250 0.8690 0.01158 0.00354 -0.0883 0.4575 1.0000
3.500 0.8925 0.01178 0.00366 -0.0875 0.4422 1.0000
3.750 0.9160 0.01199 0.00382 -0.0867 0.4270 1.0000
4.000 0.9394 0.01222 0.00398 -0.0859 0.4125 1.0000
4.250 0.9629 0.01245 0.00416 -0.0851 0.3999 1.0000
4.500 0.9862 0.01270 0.00437 -0.0843 0.3877 1.0000
4.750 1.0092 0.01297 0.00463 -0.0835 0.3759 1.0000
5.000 1.0321 0.01325 0.00488 -0.0827 0.3654 1.0000
5.250 1.0555 0.01353 0.00517 -0.0819 0.3560 1.0000
5.500 1.0783 0.01383 0.00547 -0.0811 0.3473 1.0000
5.750 1.1012 0.01414 0.00583 -0.0803 0.3380 1.0000
6.000 1.1240 0.01445 0.00619 -0.0795 0.3290 1.0000
6.500 1.1693 0.01511 0.00697 -0.0779 0.3121 1.0000
6.750 1.1913 0.01548 0.00743 -0.0770 0.3035 1.0000
7.000 1.2115 0.01587 0.00784 -0.0758 0.2813 1.0000
7.250 1.2278 0.01649 0.00825 -0.0741 0.2345 1.0000
7.500 1.2413 0.01743 0.00889 -0.0721 0.1811 1.0000
7.750 1.2468 0.01917 0.01007 -0.0691 0.1045 1.0000
8.000 1.2426 0.02166 0.01199 -0.0647 0.0179 1.0000
8.250 1.2540 0.02280 0.01332 -0.0621 0.0125 1.0000
8.500 1.2675 0.02367 0.01439 -0.0599 0.0108 1.0000
8.750 1.2773 0.02469 0.01561 -0.0572 0.0097 1.0000
9.000 1.2841 0.02585 0.01697 -0.0541 0.0090 1.0000
9.250 1.2861 0.02732 0.01863 -0.0507 0.0082 1.0000
9.500 1.2828 0.02914 0.02065 -0.0470 0.0076 1.0000
9.750 1.2871 0.03053 0.02219 -0.0445 0.0069 1.0000
10.000 1.2852 0.03244 0.02425 -0.0417 0.0066 1.0000
10.250 1.2820 0.03462 0.02658 -0.0393 0.0064 1.0000
10.500 1.2783 0.03702 0.02911 -0.0373 0.0063 1.0000
10.750 1.2740 0.03970 0.03191 -0.0357 0.0060 1.0000
11.000 1.2706 0.04249 0.03482 -0.0344 0.0059 1.0000
11.250 1.2678 0.04539 0.03782 -0.0334 0.0058 1.0000
11.500 1.2660 0.04832 0.04085 -0.0326 0.0057 1.0000
11.750 1.2647 0.05129 0.04392 -0.0317 0.0055 1.0000
12.000 1.2653 0.05417 0.04687 -0.0309 0.0054 1.0000
12.250 1.2677 0.05688 0.04972 -0.0301 0.0053 1.0000
12.500 1.2693 0.05989 0.05287 -0.0293 0.0048 1.0000
12.750 1.2716 0.06286 0.05605 -0.0289 0.0046 1.0000
13.000 1.2743 0.06587 0.05923 -0.0285 0.0045 1.0000
13.250 1.2740 0.06924 0.06280 -0.0286 0.0043 1.0000
13.500 1.2733 0.07294 0.06670 -0.0285 0.0042 1.0000
13.750 1.2700 0.07706 0.07103 -0.0289 0.0041 1.0000
14.000 1.2653 0.08136 0.07554 -0.0297 0.0041 1.0000
14.250 1.2589 0.08610 0.08050 -0.0308 0.0041 1.0000
14.500 1.2509 0.09115 0.08575 -0.0324 0.0041 1.0000
14.750 1.2412 0.09665 0.09147 -0.0344 0.0041 1.0000
15.000 1.2309 0.10242 0.09743 -0.0369 0.0041 1.0000
15.250 1.2204 0.10840 0.10360 -0.0397 0.0041 1.0000
15.500 1.2086 0.11487 0.11027 -0.0430 0.0041 1.0000
15.750 1.1975 0.12141 0.11699 -0.0465 0.0042 1.0000
16.000 1.1864 0.12821 0.12395 -0.0504 0.0042 1.0000
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Polar data table (+)
Polar graphs
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