GOE 269 AIRFOIL (goe269-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 269 AIRFOIL (goe269-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.64 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe269-il-1000000-n5.txt Download as CSV file: xf-goe269-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 269 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4297 0.11028 0.10863 -0.0051 1.0000 0.0083
-9.750 -0.4246 0.10669 0.10505 -0.0068 1.0000 0.0088
-9.500 -0.4302 0.10029 0.09866 -0.0098 1.0000 0.0099
-9.250 -0.4212 0.09785 0.09624 -0.0111 1.0000 0.0101
-9.000 -0.4122 0.09542 0.09382 -0.0125 1.0000 0.0103
-8.750 -0.4041 0.09282 0.09123 -0.0139 1.0000 0.0105
-8.500 -0.3972 0.09005 0.08847 -0.0155 1.0000 0.0108
-8.250 -0.3854 0.08628 0.08469 -0.0195 0.9668 0.0113
-8.000 -0.3797 0.07854 0.07685 -0.0281 0.9261 0.0129
-7.750 -0.3639 0.07628 0.07452 -0.0305 0.9078 0.0131
-7.500 -0.3466 0.07390 0.07208 -0.0334 0.8948 0.0134
-7.250 -0.3283 0.07112 0.06924 -0.0369 0.8827 0.0138
-7.000 -0.3088 0.06756 0.06561 -0.0415 0.8694 0.0144
-6.500 -0.2608 0.05648 0.05431 -0.0564 0.8392 0.0169
-5.500 -0.1210 0.01521 0.01086 -0.0955 0.7637 0.0250
-5.250 -0.0927 0.01347 0.00872 -0.0962 0.7422 0.0253
-5.000 -0.0645 0.01267 0.00765 -0.0964 0.7227 0.0255
-4.750 -0.0361 0.01208 0.00685 -0.0966 0.7059 0.0257
-4.500 -0.0076 0.01159 0.00618 -0.0967 0.6910 0.0258
-4.250 0.0210 0.01118 0.00561 -0.0969 0.6786 0.0259
-4.000 0.0498 0.01040 0.00461 -0.0971 0.6683 0.0264
-3.750 0.0785 0.00994 0.00402 -0.0973 0.6596 0.0268
-3.500 0.1073 0.00961 0.00361 -0.0974 0.6517 0.0273
-3.250 0.1360 0.00938 0.00330 -0.0974 0.6436 0.0277
-3.000 0.1647 0.00919 0.00306 -0.0975 0.6368 0.0283
-2.750 0.1934 0.00905 0.00287 -0.0975 0.6293 0.0289
-2.500 0.2222 0.00890 0.00267 -0.0976 0.6223 0.0295
-2.250 0.2509 0.00875 0.00247 -0.0976 0.6154 0.0301
-2.000 0.2797 0.00863 0.00230 -0.0977 0.6086 0.0306
-1.750 0.3084 0.00851 0.00214 -0.0977 0.6010 0.0312
-1.500 0.3372 0.00842 0.00200 -0.0977 0.5936 0.0316
-1.250 0.3659 0.00833 0.00188 -0.0978 0.5860 0.0320
-1.000 0.3946 0.00827 0.00178 -0.0978 0.5776 0.0324
-0.750 0.4234 0.00818 0.00165 -0.0979 0.5674 0.0338
-0.500 0.4521 0.00812 0.00158 -0.0979 0.5570 0.0357
-0.250 0.4807 0.00810 0.00153 -0.0979 0.5454 0.0378
0.000 0.5092 0.00811 0.00149 -0.0980 0.5303 0.0400
0.250 0.5376 0.00815 0.00150 -0.0980 0.5100 0.0453
0.500 0.5656 0.00826 0.00151 -0.0980 0.4825 0.0493
0.750 0.5936 0.00841 0.00158 -0.0980 0.4553 0.0539
1.000 0.6216 0.00854 0.00164 -0.0979 0.4350 0.0572
1.250 0.6497 0.00865 0.00169 -0.0979 0.4201 0.0590
1.500 0.6779 0.00873 0.00173 -0.0980 0.4059 0.0615
1.750 0.7060 0.00883 0.00179 -0.0980 0.3936 0.0639
2.000 0.7340 0.00894 0.00186 -0.0980 0.3797 0.0662
2.250 0.7620 0.00905 0.00193 -0.0979 0.3665 0.0684
2.500 0.7900 0.00915 0.00201 -0.0979 0.3549 0.0700
2.750 0.8181 0.00922 0.00205 -0.0980 0.3441 0.0730
3.000 0.8461 0.00931 0.00213 -0.0980 0.3348 0.0749
3.250 0.8742 0.00937 0.00219 -0.0980 0.3271 0.0768
3.500 0.9020 0.00947 0.00228 -0.0980 0.3187 0.0788
3.750 0.9299 0.00956 0.00237 -0.0979 0.3101 0.0805
4.000 0.9576 0.00968 0.00248 -0.0979 0.3011 0.0823
4.250 0.9852 0.00982 0.00260 -0.0979 0.2893 0.0875
4.500 1.0126 0.00998 0.00274 -0.0978 0.2753 0.0934
4.750 1.0401 0.01009 0.00294 -0.0978 0.2618 0.1604
5.250 1.0882 0.00941 0.00354 -0.0970 0.2078 1.0000
5.750 1.1390 0.01042 0.00420 -0.0964 0.1462 1.0000
6.000 1.1649 0.01080 0.00449 -0.0962 0.1303 1.0000
6.250 1.1912 0.01109 0.00475 -0.0960 0.1210 1.0000
6.500 1.2174 0.01139 0.00501 -0.0958 0.1123 1.0000
6.750 1.2433 0.01171 0.00528 -0.0956 0.1042 1.0000
7.000 1.2694 0.01198 0.00555 -0.0954 0.0978 1.0000
7.250 1.2948 0.01235 0.00587 -0.0951 0.0873 1.0000
7.500 1.3196 0.01278 0.00622 -0.0947 0.0734 1.0000
7.750 1.3431 0.01338 0.00669 -0.0942 0.0551 1.0000
8.000 1.3666 0.01395 0.00719 -0.0937 0.0418 1.0000
8.250 1.3872 0.01489 0.00797 -0.0928 0.0187 1.0000
8.500 1.4104 0.01542 0.00850 -0.0922 0.0143 1.0000
8.750 1.4336 0.01594 0.00902 -0.0916 0.0119 1.0000
9.000 1.4573 0.01636 0.00948 -0.0910 0.0110 1.0000
9.250 1.4802 0.01684 0.00999 -0.0904 0.0101 1.0000
9.500 1.5024 0.01739 0.01057 -0.0896 0.0092 1.0000
9.750 1.5241 0.01795 0.01117 -0.0888 0.0085 1.0000
10.000 1.5460 0.01845 0.01172 -0.0881 0.0081 1.0000
10.250 1.5673 0.01899 0.01230 -0.0872 0.0076 1.0000
10.500 1.5878 0.01957 0.01291 -0.0863 0.0071 1.0000
10.750 1.6072 0.02022 0.01361 -0.0852 0.0066 1.0000
11.000 1.6247 0.02101 0.01446 -0.0839 0.0062 1.0000
11.250 1.6431 0.02164 0.01515 -0.0827 0.0060 1.0000
11.500 1.6603 0.02233 0.01590 -0.0813 0.0058 1.0000
11.750 1.6760 0.02307 0.01670 -0.0797 0.0056 1.0000
12.000 1.6899 0.02385 0.01754 -0.0779 0.0054 1.0000
12.250 1.7007 0.02467 0.01845 -0.0755 0.0052 1.0000
12.500 1.7087 0.02560 0.01944 -0.0729 0.0050 1.0000
12.750 1.7161 0.02667 0.02058 -0.0704 0.0049 1.0000
13.000 1.7227 0.02791 0.02189 -0.0682 0.0047 1.0000
13.250 1.7279 0.02937 0.02343 -0.0661 0.0046 1.0000
13.500 1.7310 0.03113 0.02529 -0.0642 0.0044 1.0000
13.750 1.7321 0.03321 0.02748 -0.0625 0.0043 1.0000
14.000 1.7364 0.03511 0.02947 -0.0613 0.0042 1.0000
14.250 1.7399 0.03721 0.03168 -0.0603 0.0041 1.0000
14.500 1.7423 0.03955 0.03412 -0.0596 0.0041 1.0000
14.750 1.7430 0.04219 0.03687 -0.0590 0.0040 1.0000
15.000 1.7426 0.04508 0.03987 -0.0588 0.0039 1.0000
15.250 1.7408 0.04825 0.04314 -0.0587 0.0038 1.0000
15.500 1.7369 0.05176 0.04677 -0.0588 0.0038 1.0000
15.750 1.7312 0.05561 0.05073 -0.0591 0.0037 1.0000
16.000 1.7234 0.05980 0.05505 -0.0596 0.0037 1.0000
16.250 1.7139 0.06433 0.05970 -0.0604 0.0036 1.0000
16.500 1.7026 0.06934 0.06483 -0.0615 0.0036 1.0000
16.750 1.6908 0.07458 0.07020 -0.0628 0.0035 1.0000
17.000 1.6769 0.08034 0.07608 -0.0645 0.0035 1.0000
17.250 1.6617 0.08651 0.08239 -0.0665 0.0035 1.0000
17.500 1.6451 0.09302 0.08903 -0.0687 0.0035 1.0000
17.750 1.6280 0.09970 0.09583 -0.0711 0.0034 1.0000
18.000 1.6097 0.10673 0.10299 -0.0738 0.0034 1.0000
18.250 1.5909 0.11394 0.11032 -0.0767 0.0034 1.0000
18.500 1.5716 0.12133 0.11784 -0.0798 0.0034 1.0000
18.750 1.5530 0.12877 0.12541 -0.0832 0.0034 1.0000
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