GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 517 AIRFOIL (goe517-il) Reynolds number: 50,000 Max Cl/Cd: 40.93 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe517-il-50000-n5.txt Download as CSV file: xf-goe517-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 517 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3183 0.09885 0.09252 -0.0285 1.0000 0.0810
-7.250 -0.3221 0.09688 0.09067 -0.0276 1.0000 0.0823
-7.000 -0.3256 0.09488 0.08878 -0.0273 1.0000 0.0839
-6.750 -0.3301 0.09317 0.08718 -0.0277 1.0000 0.0856
-6.500 -0.3355 0.09203 0.08614 -0.0293 1.0000 0.0869
-6.250 -0.3382 0.09076 0.08493 -0.0314 1.0000 0.0875
-6.000 -0.3371 0.08895 0.08312 -0.0331 1.0000 0.0878
-5.750 -0.3364 0.08439 0.07869 -0.0290 1.0000 0.0888
-5.500 -0.3351 0.08129 0.07564 -0.0265 1.0000 0.0904
-5.250 -0.3327 0.07866 0.07305 -0.0254 1.0000 0.0926
-5.000 -0.3282 0.07611 0.07051 -0.0256 1.0000 0.0954
-4.750 -0.3190 0.07371 0.06806 -0.0278 1.0000 0.0995
-4.250 -0.2484 0.06191 0.05577 -0.0414 0.9881 0.0558
-4.000 -0.2160 0.05747 0.05117 -0.0459 0.9808 0.0518
-3.750 -0.1761 0.05237 0.04575 -0.0520 0.9736 0.0481
-3.500 -0.1373 0.04815 0.04119 -0.0569 0.9669 0.0482
-3.250 -0.1023 0.04463 0.03735 -0.0604 0.9592 0.0499
-3.000 -0.0657 0.04090 0.03316 -0.0636 0.9518 0.0502
-2.750 -0.0257 0.03730 0.02902 -0.0668 0.9456 0.0513
-2.500 0.0093 0.03423 0.02532 -0.0685 0.9375 0.0553
-2.250 0.0489 0.03127 0.02165 -0.0707 0.9316 0.0584
-2.000 0.0820 0.02953 0.01941 -0.0716 0.9230 0.0664
-1.750 0.1199 0.02789 0.01727 -0.0732 0.9160 0.0766
-1.500 0.1542 0.02674 0.01593 -0.0743 0.9075 0.0915
-1.250 0.1927 0.02572 0.01454 -0.0759 0.9001 0.1176
-1.000 0.2301 0.02502 0.01362 -0.0776 0.8918 0.1520
-0.750 0.2667 0.02436 0.01286 -0.0792 0.8836 0.1813
-0.500 0.3037 0.02376 0.01211 -0.0807 0.8753 0.2061
-0.250 0.3349 0.02329 0.01166 -0.0813 0.8652 0.2364
0.000 0.3724 0.02255 0.01112 -0.0831 0.8579 0.2952
0.500 0.4510 0.02088 0.01048 -0.0870 0.8382 1.0000
0.750 0.4858 0.02089 0.01021 -0.0878 0.8276 1.0000
1.000 0.5155 0.02092 0.01004 -0.0877 0.8132 1.0000
1.250 0.5449 0.02091 0.00985 -0.0874 0.7982 1.0000
1.500 0.5735 0.02091 0.00971 -0.0869 0.7829 1.0000
1.750 0.6009 0.02096 0.00964 -0.0863 0.7678 1.0000
2.000 0.6273 0.02107 0.00967 -0.0857 0.7534 1.0000
2.250 0.6534 0.02119 0.00973 -0.0850 0.7391 1.0000
2.500 0.6794 0.02132 0.00980 -0.0843 0.7248 1.0000
2.750 0.7052 0.02144 0.00991 -0.0835 0.7105 1.0000
3.000 0.7310 0.02155 0.01000 -0.0827 0.6959 1.0000
3.250 0.7568 0.02168 0.01012 -0.0819 0.6813 1.0000
3.500 0.7824 0.02181 0.01028 -0.0811 0.6662 1.0000
3.750 0.8077 0.02195 0.01044 -0.0802 0.6507 1.0000
4.000 0.8328 0.02213 0.01064 -0.0793 0.6348 1.0000
4.250 0.8577 0.02234 0.01091 -0.0785 0.6187 1.0000
4.500 0.8824 0.02258 0.01120 -0.0775 0.6020 1.0000
4.750 0.9071 0.02285 0.01153 -0.0766 0.5852 1.0000
5.000 0.9316 0.02319 0.01196 -0.0757 0.5683 1.0000
5.250 0.9559 0.02357 0.01243 -0.0748 0.5513 1.0000
5.500 0.9800 0.02402 0.01297 -0.0739 0.5343 1.0000
5.750 1.0037 0.02453 0.01363 -0.0731 0.5177 1.0000
6.000 1.0269 0.02509 0.01434 -0.0721 0.5013 1.0000
6.250 1.0497 0.02570 0.01513 -0.0712 0.4856 1.0000
6.500 1.0722 0.02635 0.01601 -0.0702 0.4706 1.0000
6.750 1.0944 0.02701 0.01689 -0.0692 0.4562 1.0000
7.000 1.1172 0.02768 0.01780 -0.0683 0.4430 1.0000
7.250 1.1392 0.02837 0.01878 -0.0672 0.4300 1.0000
7.500 1.1595 0.02918 0.01998 -0.0660 0.4169 1.0000
7.750 1.1719 0.02939 0.02036 -0.0630 0.3901 1.0000
8.000 1.1742 0.02947 0.02026 -0.0585 0.3473 1.0000
8.250 1.1712 0.03031 0.02086 -0.0539 0.2970 1.0000
8.500 1.1670 0.03164 0.02203 -0.0498 0.2358 1.0000
8.750 1.1575 0.03375 0.02359 -0.0455 0.1362 1.0000
9.000 1.1429 0.03709 0.02619 -0.0417 0.0818 1.0000
9.250 1.1351 0.04019 0.02913 -0.0388 0.0646 1.0000
9.500 1.1294 0.04314 0.03211 -0.0365 0.0559 1.0000
9.750 1.1249 0.04606 0.03519 -0.0348 0.0505 1.0000
10.000 1.1195 0.04919 0.03843 -0.0334 0.0468 1.0000
10.250 1.1163 0.05227 0.04172 -0.0323 0.0439 1.0000
10.500 1.1124 0.05554 0.04513 -0.0315 0.0413 1.0000
10.750 1.1073 0.05906 0.04873 -0.0310 0.0392 1.0000
11.000 1.1077 0.06212 0.05198 -0.0302 0.0371 1.0000
11.250 1.1102 0.06502 0.05510 -0.0294 0.0351 1.0000
11.500 1.1156 0.06769 0.05795 -0.0282 0.0336 1.0000
11.750 1.1223 0.07033 0.06075 -0.0271 0.0318 1.0000
12.000 1.1353 0.07269 0.06314 -0.0253 0.0298 1.0000
12.250 1.1428 0.07583 0.06669 -0.0245 0.0287 1.0000
12.500 1.1465 0.07954 0.07082 -0.0241 0.0280 1.0000
12.750 1.1456 0.08386 0.07547 -0.0242 0.0277 1.0000
13.000 1.1400 0.08869 0.08060 -0.0252 0.0276 1.0000
13.250 1.1309 0.09403 0.08621 -0.0268 0.0275 1.0000
13.500 1.1192 0.09991 0.09235 -0.0291 0.0275 1.0000
13.750 1.1059 0.10625 0.09891 -0.0321 0.0276 1.0000
14.000 1.0923 0.11293 0.10579 -0.0356 0.0278 1.0000
14.250 1.0780 0.12018 0.11321 -0.0397 0.0279 1.0000
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Polar data table (+)
Polar graphs
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