GOE 474 AIRFOIL (goe474-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 474 AIRFOIL (goe474-il) Reynolds number: 500,000 Max Cl/Cd: 85.07 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe474-il-500000-n5.txt Download as CSV file: xf-goe474-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 474 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4649 0.09392 0.09158 -0.0253 1.0000 0.0064
-9.500 -0.4679 0.08945 0.08715 -0.0269 1.0000 0.0066
-9.000 -0.6767 0.02993 0.02678 -0.0593 0.9968 0.0057
-8.750 -0.6544 0.02519 0.02152 -0.0622 0.9927 0.0059
-8.500 -0.6274 0.02303 0.01909 -0.0639 0.9890 0.0061
-8.250 -0.5977 0.02145 0.01729 -0.0655 0.9864 0.0064
-8.000 -0.5707 0.02024 0.01589 -0.0662 0.9819 0.0068
-7.750 -0.5420 0.01878 0.01417 -0.0672 0.9785 0.0072
-7.500 -0.5130 0.01745 0.01257 -0.0680 0.9754 0.0077
-7.250 -0.4862 0.01626 0.01115 -0.0682 0.9704 0.0080
-7.000 -0.4569 0.01497 0.00960 -0.0690 0.9671 0.0085
-6.750 -0.4274 0.01405 0.00854 -0.0697 0.9633 0.0091
-6.500 -0.3989 0.01344 0.00783 -0.0700 0.9580 0.0098
-6.250 -0.3675 0.01288 0.00717 -0.0709 0.9541 0.0109
-6.000 -0.3372 0.01239 0.00657 -0.0715 0.9494 0.0118
-5.750 -0.3083 0.01169 0.00577 -0.0718 0.9436 0.0136
-5.500 -0.2768 0.01127 0.00529 -0.0726 0.9390 0.0155
-5.250 -0.2476 0.01092 0.00487 -0.0729 0.9326 0.0175
-5.000 -0.2177 0.01050 0.00438 -0.0733 0.9262 0.0202
-4.750 -0.1889 0.01019 0.00404 -0.0735 0.9195 0.0237
-4.500 -0.1601 0.00995 0.00370 -0.0737 0.9126 0.0267
-4.250 -0.1318 0.00976 0.00345 -0.0737 0.9057 0.0286
-4.000 -0.1045 0.00940 0.00302 -0.0735 0.8982 0.0326
-3.750 -0.0772 0.00916 0.00273 -0.0733 0.8908 0.0361
-3.500 -0.0499 0.00899 0.00247 -0.0731 0.8832 0.0387
-3.250 -0.0230 0.00877 0.00222 -0.0728 0.8760 0.0449
-3.000 0.0036 0.00851 0.00202 -0.0724 0.8687 0.0622
-2.750 0.0303 0.00835 0.00192 -0.0721 0.8617 0.0892
-2.500 0.0575 0.00827 0.00183 -0.0719 0.8545 0.1012
-2.250 0.0845 0.00819 0.00175 -0.0716 0.8471 0.1088
-2.000 0.1116 0.00815 0.00166 -0.0713 0.8399 0.1152
-1.750 0.1386 0.00808 0.00158 -0.0711 0.8329 0.1204
-1.500 0.1656 0.00803 0.00150 -0.0707 0.8247 0.1252
-1.250 0.1921 0.00799 0.00142 -0.0703 0.8135 0.1295
-1.000 0.2186 0.00795 0.00135 -0.0699 0.8015 0.1341
-0.750 0.2452 0.00791 0.00130 -0.0695 0.7909 0.1399
-0.500 0.2718 0.00789 0.00125 -0.0691 0.7806 0.1460
-0.250 0.2980 0.00785 0.00121 -0.0686 0.7671 0.1564
0.000 0.3240 0.00782 0.00118 -0.0681 0.7523 0.1686
0.250 0.3501 0.00780 0.00116 -0.0677 0.7382 0.1804
0.500 0.3758 0.00779 0.00114 -0.0671 0.7204 0.1945
0.750 0.4008 0.00780 0.00113 -0.0664 0.6961 0.2161
1.000 0.4255 0.00776 0.00114 -0.0657 0.6726 0.2593
1.250 0.4464 0.00718 0.00120 -0.0645 0.6528 0.5115
1.500 0.4944 0.00623 0.00137 -0.0687 0.6225 0.9765
1.750 0.5389 0.00642 0.00143 -0.0724 0.5889 0.9964
2.000 0.5674 0.00667 0.00149 -0.0727 0.5422 1.0000
2.250 0.5860 0.00713 0.00161 -0.0708 0.4644 1.0000
2.500 0.6055 0.00760 0.00180 -0.0691 0.4051 1.0000
2.750 0.6265 0.00798 0.00198 -0.0678 0.3600 1.0000
3.000 0.6482 0.00833 0.00216 -0.0666 0.3197 1.0000
3.250 0.6703 0.00865 0.00234 -0.0655 0.2856 1.0000
3.500 0.6924 0.00897 0.00252 -0.0644 0.2519 1.0000
3.750 0.7146 0.00931 0.00272 -0.0633 0.2203 1.0000
4.000 0.7370 0.00963 0.00293 -0.0622 0.1952 1.0000
4.250 0.7598 0.00992 0.00316 -0.0613 0.1762 1.0000
4.500 0.7825 0.01023 0.00340 -0.0603 0.1588 1.0000
4.750 0.8056 0.01052 0.00364 -0.0594 0.1447 1.0000
5.000 0.8288 0.01080 0.00389 -0.0585 0.1309 1.0000
5.250 0.8521 0.01108 0.00414 -0.0577 0.1196 1.0000
5.500 0.8754 0.01137 0.00441 -0.0568 0.1089 1.0000
5.750 0.8981 0.01171 0.00470 -0.0559 0.0963 1.0000
6.000 0.9209 0.01206 0.00500 -0.0550 0.0856 1.0000
6.250 0.9438 0.01239 0.00534 -0.0541 0.0765 1.0000
6.500 0.9669 0.01270 0.00566 -0.0533 0.0678 1.0000
6.750 0.9891 0.01311 0.00601 -0.0523 0.0534 1.0000
7.000 1.0093 0.01372 0.00649 -0.0511 0.0342 1.0000
7.250 1.0293 0.01437 0.00706 -0.0499 0.0210 1.0000
7.500 1.0502 0.01493 0.00764 -0.0487 0.0156 1.0000
7.750 1.0714 0.01546 0.00822 -0.0476 0.0127 1.0000
8.000 1.0925 0.01599 0.00882 -0.0464 0.0110 1.0000
8.250 1.1126 0.01662 0.00949 -0.0452 0.0097 1.0000
8.500 1.1319 0.01735 0.01030 -0.0438 0.0087 1.0000
8.750 1.1520 0.01795 0.01100 -0.0426 0.0082 1.0000
9.000 1.1712 0.01863 0.01177 -0.0413 0.0076 1.0000
9.250 1.1897 0.01934 0.01257 -0.0399 0.0071 1.0000
9.500 1.2076 0.02009 0.01341 -0.0384 0.0066 1.0000
9.750 1.2222 0.02114 0.01455 -0.0365 0.0062 1.0000
10.000 1.2383 0.02197 0.01548 -0.0349 0.0058 1.0000
10.250 1.2539 0.02279 0.01642 -0.0331 0.0055 1.0000
10.500 1.2664 0.02380 0.01755 -0.0309 0.0053 1.0000
10.750 1.2773 0.02475 0.01861 -0.0285 0.0051 1.0000
11.000 1.2861 0.02581 0.01979 -0.0258 0.0049 1.0000
11.250 1.2950 0.02685 0.02094 -0.0233 0.0047 1.0000
11.500 1.3021 0.02804 0.02225 -0.0207 0.0046 1.0000
11.750 1.3083 0.02929 0.02362 -0.0183 0.0045 1.0000
12.000 1.3138 0.03060 0.02503 -0.0160 0.0043 1.0000
12.250 1.3153 0.03231 0.02687 -0.0135 0.0043 1.0000
12.500 1.3124 0.03445 0.02919 -0.0110 0.0041 1.0000
12.750 1.3079 0.03687 0.03177 -0.0089 0.0040 1.0000
13.000 1.3035 0.03944 0.03450 -0.0071 0.0040 1.0000
13.250 1.3034 0.04171 0.03695 -0.0060 0.0039 1.0000
13.500 1.2976 0.04474 0.04016 -0.0051 0.0039 1.0000
13.750 1.2908 0.04811 0.04372 -0.0047 0.0038 1.0000
14.000 1.2810 0.05209 0.04789 -0.0050 0.0038 1.0000
14.250 1.2705 0.05648 0.05246 -0.0059 0.0038 1.0000
14.500 1.2585 0.06150 0.05765 -0.0076 0.0037 1.0000
14.750 1.2428 0.06754 0.06387 -0.0102 0.0038 1.0000
15.000 1.2269 0.07432 0.07082 -0.0138 0.0038 1.0000
15.250 1.2104 0.08199 0.07866 -0.0183 0.0038 1.0000
15.500 1.1904 0.09092 0.08777 -0.0236 0.0037 1.0000
15.750 1.1689 0.10027 0.09726 -0.0290 0.0038 1.0000
16.000 1.1477 0.10989 0.10701 -0.0344 0.0038 1.0000
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