GOE 495 AIRFOIL (goe495-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 495 AIRFOIL (goe495-il) Reynolds number: 50,000 Max Cl/Cd: 45.24 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe495-il-50000-n5.txt Download as CSV file: xf-goe495-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 495 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3370 0.10456 0.09798 -0.0315 1.0000 0.1018
-7.500 -0.3508 0.10401 0.09758 -0.0301 1.0000 0.1028
-7.250 -0.3624 0.10306 0.09678 -0.0299 1.0000 0.1034
-7.000 -0.3690 0.10146 0.09529 -0.0305 1.0000 0.1037
-6.750 -0.3726 0.09937 0.09328 -0.0317 1.0000 0.1039
-6.500 -0.3714 0.09602 0.09002 -0.0305 1.0000 0.1042
-6.000 -0.3612 0.08535 0.07930 -0.0365 1.0000 0.0619
-5.750 -0.3592 0.08251 0.07650 -0.0334 1.0000 0.0610
-5.500 -0.3533 0.07923 0.07324 -0.0347 1.0000 0.0606
-5.250 -0.3441 0.07558 0.06960 -0.0371 1.0000 0.0604
-5.000 -0.3315 0.07161 0.06560 -0.0403 1.0000 0.0601
-4.500 -0.2814 0.06185 0.05562 -0.0518 0.9964 0.0577
-4.250 -0.2335 0.05477 0.04824 -0.0636 0.9921 0.0577
-4.000 -0.1699 0.04555 0.03827 -0.0794 0.9892 0.0610
-3.750 -0.1150 0.03878 0.03062 -0.0895 0.9871 0.0623
-3.500 -0.0812 0.03700 0.02873 -0.0924 0.9820 0.0683
-3.250 -0.0327 0.03297 0.02371 -0.0984 0.9792 0.0738
-3.000 0.0087 0.03040 0.02051 -0.1019 0.9757 0.0778
-2.750 0.0451 0.02921 0.01892 -0.1043 0.9702 0.0879
-2.500 0.0838 0.02780 0.01715 -0.1067 0.9661 0.0932
-2.250 0.1170 0.02680 0.01583 -0.1079 0.9598 0.0997
-2.000 0.1546 0.02599 0.01476 -0.1099 0.9548 0.1098
-1.750 0.1887 0.02543 0.01401 -0.1112 0.9484 0.1299
-1.500 0.2252 0.02495 0.01353 -0.1132 0.9425 0.1739
-1.250 0.2606 0.02460 0.01333 -0.1151 0.9364 0.2403
-1.000 0.2933 0.02443 0.01338 -0.1165 0.9293 0.3185
-0.750 0.3288 0.02417 0.01326 -0.1181 0.9233 0.3906
-0.500 0.3592 0.02392 0.01321 -0.1188 0.9156 0.4718
-0.250 0.3934 0.02337 0.01311 -0.1199 0.9102 0.6069
0.000 0.4155 0.02275 0.01289 -0.1184 0.9002 1.0000
0.250 0.4490 0.02304 0.01287 -0.1197 0.8924 1.0000
0.500 0.4832 0.02330 0.01289 -0.1210 0.8848 1.0000
0.750 0.5132 0.02361 0.01302 -0.1216 0.8760 1.0000
1.000 0.5501 0.02381 0.01307 -0.1233 0.8694 1.0000
1.250 0.5773 0.02415 0.01332 -0.1234 0.8595 1.0000
1.500 0.6125 0.02436 0.01344 -0.1247 0.8526 1.0000
1.750 0.6422 0.02464 0.01369 -0.1251 0.8433 1.0000
2.000 0.6709 0.02496 0.01400 -0.1253 0.8338 1.0000
2.250 0.7074 0.02506 0.01410 -0.1266 0.8270 1.0000
2.500 0.7330 0.02541 0.01448 -0.1262 0.8158 1.0000
2.750 0.7616 0.02567 0.01481 -0.1263 0.8057 1.0000
3.000 0.7976 0.02568 0.01489 -0.1272 0.7979 1.0000
3.500 0.8494 0.02627 0.01570 -0.1262 0.7741 1.0000
3.750 0.8789 0.02643 0.01598 -0.1261 0.7636 1.0000
4.000 0.9116 0.02643 0.01615 -0.1263 0.7541 1.0000
4.250 0.9366 0.02671 0.01658 -0.1255 0.7411 1.0000
4.500 0.9639 0.02678 0.01687 -0.1247 0.7272 1.0000
4.750 0.9935 0.02655 0.01684 -0.1240 0.7116 1.0000
5.000 1.0201 0.02630 0.01678 -0.1225 0.6920 1.0000
5.250 1.0467 0.02602 0.01673 -0.1210 0.6708 1.0000
5.500 1.0748 0.02579 0.01671 -0.1197 0.6508 1.0000
5.750 1.0983 0.02587 0.01704 -0.1181 0.6290 1.0000
6.000 1.1229 0.02576 0.01714 -0.1163 0.6016 1.0000
6.250 1.1444 0.02549 0.01696 -0.1135 0.5556 1.0000
6.500 1.1587 0.02561 0.01688 -0.1097 0.4862 1.0000
6.750 1.1691 0.02634 0.01729 -0.1060 0.4017 1.0000
7.000 1.1766 0.02767 0.01815 -0.1025 0.3186 1.0000
7.250 1.1781 0.02970 0.01959 -0.0989 0.2329 1.0000
7.500 1.1780 0.03206 0.02142 -0.0955 0.1740 1.0000
7.750 1.1811 0.03433 0.02349 -0.0925 0.1380 1.0000
8.000 1.1866 0.03653 0.02561 -0.0897 0.1137 1.0000
8.250 1.1935 0.03860 0.02766 -0.0874 0.0954 1.0000
8.500 1.2020 0.04067 0.02972 -0.0852 0.0822 1.0000
8.750 1.2136 0.04273 0.03188 -0.0833 0.0709 1.0000
9.000 1.2305 0.04491 0.03420 -0.0817 0.0624 1.0000
9.250 1.2464 0.04716 0.03645 -0.0803 0.0549 1.0000
9.500 1.2772 0.04985 0.03952 -0.0798 0.0487 1.0000
9.750 1.2954 0.05248 0.04227 -0.0789 0.0441 1.0000
10.000 1.3159 0.05601 0.04613 -0.0781 0.0407 1.0000
10.250 1.3295 0.05980 0.05044 -0.0766 0.0389 1.0000
10.500 1.3332 0.06340 0.05455 -0.0744 0.0374 1.0000
10.750 1.3317 0.06682 0.05830 -0.0722 0.0360 1.0000
11.000 1.3273 0.07023 0.06198 -0.0701 0.0348 1.0000
11.250 1.3206 0.07381 0.06579 -0.0683 0.0339 1.0000
11.500 1.3121 0.07778 0.06998 -0.0670 0.0331 1.0000
11.750 1.3006 0.08229 0.07471 -0.0661 0.0327 1.0000
12.000 1.2858 0.08721 0.07989 -0.0657 0.0325 1.0000
12.250 1.2684 0.09245 0.08534 -0.0660 0.0324 1.0000
12.750 1.2272 0.10452 0.09801 -0.0698 0.0327 1.0000
13.000 1.1937 0.11389 0.10774 -0.0755 0.0339 1.0000
13.250 1.1471 0.12939 0.12343 -0.0865 0.0371 1.0000
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Polar data table (+)
Polar graphs
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