GOE 491 AIRFOIL (goe491-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 491 AIRFOIL (goe491-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.98 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe491-il-1000000.txt Download as CSV file: xf-goe491-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 491 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5024 0.09369 0.09206 -0.0011 1.0000 0.0078
-8.250 -0.5000 0.09056 0.08895 -0.0023 1.0000 0.0078
-8.000 -0.5003 0.08729 0.08570 -0.0037 1.0000 0.0078
-7.750 -0.5003 0.08489 0.08332 -0.0041 1.0000 0.0080
-7.500 -0.4986 0.08146 0.07990 -0.0060 1.0000 0.0080
-7.250 -0.4924 0.07842 0.07687 -0.0079 1.0000 0.0083
-7.000 -0.4857 0.07485 0.07328 -0.0101 1.0000 0.0084
-5.500 -0.4069 0.05158 0.04973 -0.0204 1.0000 0.0111
-4.500 -0.3584 0.01355 0.00941 -0.0180 0.9959 0.0086
-4.250 -0.3253 0.01231 0.00795 -0.0191 0.9942 0.0094
-4.000 -0.2944 0.01124 0.00665 -0.0197 0.9916 0.0102
-3.750 -0.2611 0.01053 0.00579 -0.0208 0.9886 0.0108
-3.500 -0.2264 0.00999 0.00516 -0.0222 0.9857 0.0112
-3.250 -0.1937 0.00856 0.00348 -0.0231 0.9833 0.0126
-3.000 -0.1658 0.00814 0.00303 -0.0230 0.9768 0.0143
-2.750 -0.1329 0.00775 0.00257 -0.0239 0.9720 0.0159
-2.500 -0.1046 0.00733 0.00209 -0.0238 0.9627 0.0178
-2.250 -0.0709 0.00692 0.00171 -0.0249 0.9552 0.0268
-2.000 -0.0303 0.00687 0.00178 -0.0277 0.9456 0.0424
-1.750 0.0139 0.00677 0.00164 -0.0313 0.9331 0.0471
-1.500 0.0551 0.00666 0.00150 -0.0343 0.9127 0.0518
-1.250 0.0863 0.00671 0.00147 -0.0349 0.8898 0.0555
-1.000 0.1133 0.00676 0.00144 -0.0345 0.8663 0.0570
-0.750 0.1376 0.00661 0.00120 -0.0335 0.8387 0.0620
-0.500 0.1611 0.00663 0.00108 -0.0323 0.7955 0.0644
-0.250 0.1833 0.00676 0.00098 -0.0309 0.7374 0.0665
0.000 0.2059 0.00691 0.00090 -0.0296 0.6807 0.0688
0.250 0.2290 0.00709 0.00086 -0.0285 0.6226 0.0708
0.500 0.2520 0.00721 0.00080 -0.0274 0.5620 0.0797
0.750 0.2751 0.00743 0.00078 -0.0264 0.4927 0.0887
1.000 0.2993 0.00753 0.00080 -0.0256 0.4531 0.1119
1.250 0.3200 0.00704 0.00088 -0.0244 0.4325 0.3701
1.500 0.4081 0.00584 0.00120 -0.0384 0.4074 0.9908
1.750 0.4674 0.00602 0.00126 -0.0456 0.3827 0.9985
2.000 0.5016 0.00612 0.00127 -0.0470 0.3653 1.0000
2.250 0.5259 0.00621 0.00130 -0.0462 0.3467 1.0000
2.500 0.5499 0.00634 0.00133 -0.0454 0.3238 1.0000
2.750 0.5736 0.00652 0.00139 -0.0445 0.2904 1.0000
3.000 0.5960 0.00684 0.00149 -0.0435 0.2389 1.0000
3.250 0.6172 0.00733 0.00167 -0.0422 0.1722 1.0000
3.500 0.6364 0.00810 0.00198 -0.0407 0.0747 1.0000
3.750 0.6583 0.00856 0.00226 -0.0395 0.0389 1.0000
4.000 0.6822 0.00876 0.00249 -0.0386 0.0359 1.0000
4.250 0.7060 0.00897 0.00272 -0.0377 0.0346 1.0000
4.500 0.7296 0.00921 0.00301 -0.0368 0.0331 1.0000
4.750 0.7529 0.00951 0.00337 -0.0358 0.0317 1.0000
5.000 0.7765 0.00972 0.00361 -0.0349 0.0311 1.0000
5.250 0.8001 0.00995 0.00387 -0.0341 0.0302 1.0000
5.500 0.8233 0.01022 0.00419 -0.0331 0.0288 1.0000
5.750 0.8464 0.01051 0.00451 -0.0322 0.0267 1.0000
6.000 0.8688 0.01089 0.00491 -0.0311 0.0242 1.0000
6.250 0.8873 0.01177 0.00592 -0.0293 0.0211 1.0000
6.500 0.9128 0.01173 0.00588 -0.0289 0.0201 1.0000
6.750 0.9370 0.01184 0.00600 -0.0282 0.0180 1.0000
7.000 0.9609 0.01200 0.00612 -0.0275 0.0158 1.0000
7.250 0.9811 0.01265 0.00683 -0.0261 0.0137 1.0000
7.500 1.0040 0.01292 0.00713 -0.0251 0.0126 1.0000
7.750 1.0265 0.01325 0.00749 -0.0242 0.0113 1.0000
8.000 1.0462 0.01392 0.00820 -0.0227 0.0101 1.0000
8.250 1.0620 0.01508 0.00952 -0.0206 0.0091 1.0000
8.500 1.0842 0.01542 0.00991 -0.0196 0.0086 1.0000
8.750 1.1047 0.01595 0.01051 -0.0184 0.0080 1.0000
9.000 1.1247 0.01654 0.01116 -0.0171 0.0074 1.0000
9.250 1.1435 0.01724 0.01194 -0.0157 0.0069 1.0000
9.500 1.1595 0.01830 0.01312 -0.0138 0.0066 1.0000
9.750 1.1681 0.02031 0.01537 -0.0108 0.0061 1.0000
10.000 1.1754 0.02260 0.01794 -0.0078 0.0059 1.0000
10.250 1.1906 0.02370 0.01919 -0.0061 0.0058 1.0000
10.500 1.2049 0.02485 0.02049 -0.0043 0.0056 1.0000
10.750 1.2159 0.02637 0.02220 -0.0021 0.0055 1.0000
11.000 1.2269 0.02773 0.02373 0.0000 0.0052 1.0000
11.250 1.2325 0.02961 0.02582 0.0026 0.0050 1.0000
11.500 1.2387 0.03115 0.02752 0.0050 0.0048 1.0000
11.750 1.2351 0.03326 0.02983 0.0086 0.0047 1.0000
12.000 1.2332 0.03473 0.03145 0.0119 0.0046 1.0000
12.250 1.2325 0.03626 0.03310 0.0143 0.0044 1.0000
12.500 1.2197 0.03935 0.03640 0.0161 0.0044 1.0000
12.750 1.2204 0.04135 0.03848 0.0164 0.0043 1.0000
13.000 1.2201 0.04385 0.04108 0.0158 0.0042 1.0000
13.250 1.1884 0.05192 0.04945 0.0115 0.0042 1.0000
13.500 1.1977 0.05411 0.05165 0.0096 0.0041 1.0000
13.750 1.0810 0.08204 0.08017 -0.0089 0.0048 1.0000
14.000 1.0403 0.09565 0.09393 -0.0169 0.0050 1.0000
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Polar data table (+)
Polar graphs
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