GOE 410 AIRFOIL (goe410-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 410 AIRFOIL (goe410-il) Reynolds number: 100,000 Max Cl/Cd: 37.12 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe410-il-100000.txt Download as CSV file: xf-goe410-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 410 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.9056 0.07927 0.07302 -0.0251 1.0000 0.1433
-13.000 -0.9907 0.06625 0.05974 -0.0318 1.0000 0.1417
-12.750 -1.0454 0.05942 0.05265 -0.0331 1.0000 0.1412
-12.500 -1.0855 0.05524 0.04820 -0.0312 1.0000 0.1418
-12.250 -1.1160 0.05219 0.04484 -0.0278 1.0000 0.1429
-12.000 -1.1377 0.04948 0.04172 -0.0246 1.0000 0.1444
-11.750 -1.1040 0.04757 0.04006 -0.0255 1.0000 0.1489
-11.500 -1.0927 0.04594 0.03837 -0.0244 1.0000 0.1527
-11.250 -1.0938 0.04384 0.03598 -0.0223 1.0000 0.1558
-11.000 -1.0971 0.04197 0.03365 -0.0197 1.0000 0.1586
-10.750 -1.0749 0.03980 0.03160 -0.0197 1.0000 0.1627
-10.500 -1.0561 0.03849 0.03027 -0.0189 1.0000 0.1670
-10.250 -1.0437 0.03698 0.02854 -0.0176 1.0000 0.1710
-10.000 -1.0349 0.03559 0.02675 -0.0157 1.0000 0.1743
-9.750 -1.0095 0.03366 0.02498 -0.0157 1.0000 0.1782
-9.500 -0.9885 0.03241 0.02370 -0.0151 1.0000 0.1822
-9.250 -0.9698 0.03114 0.02227 -0.0141 1.0000 0.1863
-9.000 -0.9526 0.02996 0.02080 -0.0128 1.0000 0.1898
-8.750 -0.9265 0.02846 0.01946 -0.0127 1.0000 0.1939
-8.500 -0.9031 0.02743 0.01848 -0.0122 1.0000 0.1987
-8.250 -0.8821 0.02643 0.01734 -0.0113 1.0000 0.2037
-8.000 -0.8588 0.02529 0.01623 -0.0107 1.0000 0.2085
-7.750 -0.8351 0.02439 0.01546 -0.0101 1.0000 0.2144
-7.500 -0.8142 0.02357 0.01453 -0.0090 1.0000 0.2214
-7.250 -0.7916 0.02267 0.01386 -0.0082 1.0000 0.2286
-7.000 -0.7712 0.02194 0.01310 -0.0071 1.0000 0.2374
-6.750 -0.7511 0.02117 0.01255 -0.0059 1.0000 0.2465
-6.500 -0.7330 0.02049 0.01198 -0.0044 1.0000 0.2581
-6.250 -0.7170 0.01989 0.01149 -0.0026 1.0000 0.2723
-6.000 -0.7040 0.01935 0.01112 -0.0004 1.0000 0.2888
-5.750 -0.6956 0.01890 0.01090 0.0024 1.0000 0.3077
-5.500 -0.6908 0.01861 0.01085 0.0056 1.0000 0.3296
-5.250 -0.6689 0.01851 0.01098 0.0055 0.9939 0.3655
-5.000 -0.6143 0.01878 0.01133 0.0002 0.9759 0.4131
-4.750 -0.5595 0.01921 0.01188 -0.0045 0.9592 0.4433
-4.500 -0.5070 0.01944 0.01203 -0.0088 0.9424 0.4686
-4.250 -0.4598 0.01962 0.01223 -0.0118 0.9237 0.4877
-4.000 -0.4180 0.01979 0.01249 -0.0134 0.9037 0.5030
-3.750 -0.3831 0.01987 0.01258 -0.0138 0.8828 0.5162
-3.500 -0.3549 0.01985 0.01244 -0.0132 0.8622 0.5294
-3.250 -0.3277 0.01995 0.01254 -0.0121 0.8425 0.5400
-3.000 -0.3034 0.01993 0.01243 -0.0109 0.8238 0.5509
-2.750 -0.2788 0.02002 0.01249 -0.0096 0.8063 0.5623
-2.500 -0.2541 0.02005 0.01251 -0.0084 0.7900 0.5725
-2.250 -0.2297 0.02005 0.01243 -0.0074 0.7752 0.5835
-2.000 -0.2042 0.02006 0.01243 -0.0062 0.7626 0.5928
-1.750 -0.1797 0.02004 0.01234 -0.0054 0.7488 0.6043
-1.500 -0.1538 0.02005 0.01239 -0.0045 0.7364 0.6127
-1.250 -0.1288 0.02001 0.01224 -0.0036 0.7260 0.6240
-1.000 -0.1030 0.02008 0.01240 -0.0028 0.7135 0.6336
-0.750 -0.0779 0.02004 0.01223 -0.0019 0.7045 0.6459
-0.500 -0.0517 0.02011 0.01243 -0.0012 0.6930 0.6543
-0.250 -0.0261 0.02004 0.01222 -0.0006 0.6847 0.6656
0.000 0.0000 0.02010 0.01240 0.0000 0.6734 0.6734
0.250 0.0261 0.02004 0.01221 0.0006 0.6655 0.6847
0.500 0.0517 0.02011 0.01243 0.0012 0.6543 0.6929
0.750 0.0779 0.02004 0.01223 0.0019 0.6459 0.7045
1.000 0.1030 0.02008 0.01239 0.0028 0.6335 0.7136
1.250 0.1287 0.02001 0.01224 0.0036 0.6240 0.7260
1.500 0.1538 0.02005 0.01239 0.0045 0.6127 0.7364
1.750 0.1798 0.02004 0.01234 0.0054 0.6043 0.7488
2.000 0.2043 0.02006 0.01242 0.0062 0.5928 0.7626
2.250 0.2297 0.02005 0.01243 0.0074 0.5835 0.7752
2.500 0.2541 0.02006 0.01252 0.0084 0.5726 0.7900
2.750 0.2788 0.02002 0.01249 0.0096 0.5623 0.8062
3.000 0.3034 0.01992 0.01243 0.0109 0.5509 0.8238
3.250 0.3277 0.01995 0.01254 0.0121 0.5400 0.8425
3.500 0.3549 0.01985 0.01243 0.0132 0.5294 0.8622
3.750 0.3831 0.01987 0.01258 0.0138 0.5162 0.8828
4.000 0.4180 0.01979 0.01249 0.0134 0.5031 0.9037
4.250 0.4598 0.01962 0.01223 0.0118 0.4877 0.9237
4.500 0.5070 0.01944 0.01203 0.0088 0.4687 0.9424
4.750 0.5596 0.01921 0.01188 0.0045 0.4433 0.9593
5.000 0.6143 0.01878 0.01132 -0.0002 0.4131 0.9759
5.250 0.6690 0.01851 0.01098 -0.0055 0.3654 0.9939
5.500 0.6908 0.01861 0.01085 -0.0056 0.3297 1.0000
5.750 0.6955 0.01890 0.01090 -0.0024 0.3077 1.0000
6.000 0.7040 0.01935 0.01112 0.0004 0.2889 1.0000
6.250 0.7170 0.01989 0.01150 0.0026 0.2724 1.0000
6.500 0.7330 0.02049 0.01198 0.0044 0.2581 1.0000
6.750 0.7511 0.02117 0.01255 0.0059 0.2465 1.0000
7.000 0.7713 0.02193 0.01310 0.0071 0.2375 1.0000
7.250 0.7916 0.02267 0.01385 0.0082 0.2286 1.0000
7.500 0.8142 0.02356 0.01453 0.0090 0.2213 1.0000
7.750 0.8352 0.02439 0.01546 0.0100 0.2144 1.0000
8.000 0.8588 0.02529 0.01623 0.0107 0.2086 1.0000
8.250 0.8822 0.02643 0.01734 0.0113 0.2037 1.0000
8.500 0.9032 0.02744 0.01848 0.0122 0.1987 1.0000
8.750 0.9265 0.02846 0.01946 0.0127 0.1939 1.0000
9.000 0.9526 0.02996 0.02080 0.0128 0.1898 1.0000
9.250 0.9699 0.03114 0.02227 0.0141 0.1863 1.0000
9.500 0.9885 0.03241 0.02370 0.0151 0.1822 1.0000
9.750 1.0095 0.03366 0.02498 0.0157 0.1782 1.0000
10.000 1.0348 0.03558 0.02675 0.0157 0.1742 1.0000
10.250 1.0438 0.03697 0.02854 0.0175 0.1710 1.0000
10.500 1.0562 0.03848 0.03027 0.0189 0.1669 1.0000
10.750 1.0751 0.03978 0.03157 0.0197 0.1626 1.0000
11.000 1.0972 0.04197 0.03365 0.0197 0.1586 1.0000
11.250 1.0939 0.04384 0.03597 0.0223 0.1558 1.0000
11.500 1.0930 0.04593 0.03835 0.0244 0.1526 1.0000
11.750 1.1047 0.04753 0.04002 0.0254 0.1489 1.0000
12.000 1.1376 0.04947 0.04171 0.0246 0.1445 1.0000
12.250 1.1160 0.05218 0.04483 0.0278 0.1428 1.0000
12.500 1.0858 0.05525 0.04821 0.0312 0.1418 1.0000
12.750 1.0458 0.05944 0.05267 0.0331 0.1412 1.0000
13.000 0.9902 0.06633 0.05983 0.0317 0.1417 1.0000
13.250 0.9048 0.07946 0.07321 0.0249 0.1433 1.0000
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