GOE 396 AIRFOIL (goe396-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 396 AIRFOIL (goe396-il) Reynolds number: 1,000,000 Max Cl/Cd: 141.69 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe396-il-1000000.txt Download as CSV file: xf-goe396-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 396 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3135 0.10365 0.10207 -0.0274 1.0000 0.0059
-8.500 -0.3103 0.10100 0.09943 -0.0276 1.0000 0.0059
-8.250 -0.3077 0.09858 0.09703 -0.0276 1.0000 0.0059
-8.000 -0.2129 0.07760 0.07618 -0.0380 0.9933 0.0062
-7.750 -0.2012 0.07372 0.07230 -0.0406 0.9876 0.0063
-7.500 -0.1873 0.06981 0.06839 -0.0437 0.9820 0.0065
-7.250 -0.1725 0.06579 0.06436 -0.0475 0.9736 0.0066
-7.000 -0.2496 0.07995 0.07847 -0.0438 0.9843 0.0062
-6.750 -0.2299 0.07629 0.07481 -0.0481 0.9763 0.0064
-6.500 -0.2020 0.07230 0.07079 -0.0548 0.9700 0.0066
-6.250 -0.1701 0.06822 0.06668 -0.0624 0.9621 0.0070
-4.250 0.0576 0.03619 0.03376 -0.1037 0.8422 0.0113
-4.000 0.0819 0.03445 0.03192 -0.1048 0.8342 0.0123
-3.750 0.1093 0.03177 0.02913 -0.1065 0.8263 0.0137
-2.750 0.2169 0.01011 0.00534 -0.1083 0.7986 0.0100
-2.500 0.2413 0.00834 0.00316 -0.1074 0.7912 0.0123
-2.250 0.2681 0.00810 0.00286 -0.1071 0.7839 0.0139
-2.000 0.2948 0.00787 0.00254 -0.1067 0.7767 0.0158
-1.750 0.3208 0.00739 0.00196 -0.1062 0.7681 0.0195
-1.500 0.3474 0.00725 0.00178 -0.1058 0.7588 0.0238
-1.250 0.3743 0.00728 0.00176 -0.1055 0.7496 0.0265
-1.000 0.4003 0.00692 0.00133 -0.1051 0.7400 0.0339
-0.750 0.4269 0.00683 0.00118 -0.1047 0.7297 0.0376
-0.500 0.4533 0.00679 0.00109 -0.1044 0.7171 0.0393
-0.250 0.4794 0.00667 0.00087 -0.1039 0.7038 0.0441
0.000 0.5053 0.00655 0.00077 -0.1035 0.6905 0.0645
0.250 0.5312 0.00648 0.00078 -0.1031 0.6767 0.1148
0.500 0.5574 0.00650 0.00078 -0.1027 0.6625 0.1283
0.750 0.5835 0.00653 0.00078 -0.1023 0.6484 0.1406
1.000 0.6095 0.00657 0.00079 -0.1019 0.6343 0.1554
1.250 0.6355 0.00659 0.00083 -0.1016 0.6209 0.1775
1.500 0.6614 0.00661 0.00088 -0.1012 0.6071 0.2132
1.750 0.6869 0.00661 0.00095 -0.1008 0.5918 0.2671
2.000 0.7118 0.00652 0.00106 -0.1003 0.5769 0.3844
2.250 0.7696 0.00547 0.00122 -0.1078 0.5573 1.0000
2.500 0.7949 0.00561 0.00129 -0.1072 0.5400 1.0000
2.750 0.8184 0.00587 0.00139 -0.1064 0.5042 1.0000
3.000 0.8415 0.00617 0.00151 -0.1055 0.4654 1.0000
3.250 0.8629 0.00664 0.00172 -0.1043 0.4052 1.0000
3.500 0.8822 0.00732 0.00200 -0.1028 0.3244 1.0000
3.750 0.8934 0.00880 0.00266 -0.1001 0.1501 1.0000
4.000 0.9156 0.00925 0.00295 -0.0991 0.1193 1.0000
4.250 0.9390 0.00958 0.00318 -0.0984 0.0982 1.0000
4.500 0.9565 0.01052 0.00372 -0.0966 0.0162 1.0000
4.750 0.9802 0.01084 0.00414 -0.0957 0.0128 1.0000
5.000 1.0026 0.01129 0.00471 -0.0946 0.0110 1.0000
5.250 1.0256 0.01166 0.00511 -0.0936 0.0102 1.0000
5.500 1.0478 0.01209 0.00559 -0.0926 0.0092 1.0000
5.750 1.0691 0.01263 0.00621 -0.0913 0.0085 1.0000
6.000 1.0896 0.01322 0.00686 -0.0900 0.0078 1.0000
6.250 1.1084 0.01397 0.00769 -0.0883 0.0069 1.0000
6.500 1.1183 0.01562 0.00946 -0.0851 0.0062 1.0000
6.750 1.1312 0.01709 0.01100 -0.0824 0.0061 1.0000
7.000 1.1490 0.01814 0.01211 -0.0805 0.0062 1.0000
7.250 1.1681 0.01915 0.01319 -0.0790 0.0064 1.0000
7.500 1.1860 0.02174 0.01583 -0.0774 0.0061 1.0000
7.750 1.2079 0.02353 0.01771 -0.0764 0.0061 1.0000
8.250 1.2457 0.02603 0.02060 -0.0734 0.0052 1.0000
8.500 1.2645 0.02789 0.02263 -0.0718 0.0050 1.0000
8.750 1.2814 0.03059 0.02558 -0.0698 0.0048 1.0000
9.500 1.2833 0.04693 0.04298 -0.0595 0.0058 1.0000
9.750 1.2811 0.04972 0.04601 -0.0560 0.0057 1.0000
10.000 1.2755 0.05241 0.04891 -0.0523 0.0057 1.0000
10.250 1.2648 0.05427 0.05097 -0.0477 0.0057 1.0000
10.500 1.2504 0.05684 0.05368 -0.0434 0.0057 1.0000
10.750 1.2371 0.05877 0.05577 -0.0399 0.0056 1.0000
11.000 1.2468 0.05837 0.05549 -0.0379 0.0050 1.0000
11.250 1.2326 0.06158 0.05885 -0.0360 0.0049 1.0000
11.500 1.2166 0.06532 0.06275 -0.0348 0.0048 1.0000
11.750 1.1990 0.06966 0.06724 -0.0346 0.0048 1.0000
12.000 1.1804 0.07463 0.07235 -0.0352 0.0048 1.0000
12.500 1.1400 0.08672 0.08470 -0.0398 0.0049 1.0000
12.750 0.9737 0.10224 0.10044 -0.0454 0.0058 1.0000
13.000 0.9461 0.10913 0.10745 -0.0503 0.0058 1.0000
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Polar data table (+)
Polar graphs
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