GOE 500 AIRFOIL (goe500-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 500 AIRFOIL (goe500-il) Reynolds number: 50,000 Max Cl/Cd: 36.26 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe500-il-50000-n5.txt Download as CSV file: xf-goe500-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 500 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3309 0.12168 0.11514 -0.0319 1.0000 0.1126
-8.500 -0.3435 0.12077 0.11432 -0.0308 1.0000 0.1132
-8.250 -0.3548 0.11950 0.11315 -0.0295 1.0000 0.1134
-8.000 -0.3655 0.11806 0.11179 -0.0279 1.0000 0.1135
-7.750 -0.3744 0.11630 0.11012 -0.0265 0.9997 0.1135
-7.500 -0.3649 0.10854 0.10228 -0.0316 0.9942 0.0845
-7.250 -0.3508 0.10450 0.09821 -0.0339 0.9888 0.0838
-7.000 -0.3370 0.10052 0.09421 -0.0375 0.9830 0.0832
-6.750 -0.3232 0.09655 0.09022 -0.0407 0.9768 0.0816
-6.500 -0.3104 0.09240 0.08605 -0.0448 0.9698 0.0796
-6.250 -0.2941 0.08784 0.08146 -0.0506 0.9629 0.0787
-6.000 -0.2808 0.08386 0.07745 -0.0555 0.9550 0.0800
-5.750 -0.2583 0.07887 0.07239 -0.0632 0.9486 0.0811
-5.500 -0.2412 0.07424 0.06769 -0.0690 0.9408 0.0808
-5.250 -0.2128 0.06846 0.06176 -0.0778 0.9349 0.0805
-5.000 -0.1773 0.06122 0.05426 -0.0899 0.9290 0.0825
-4.750 -0.1258 0.05060 0.04286 -0.1077 0.9239 0.0848
-4.500 -0.0885 0.04688 0.03883 -0.1133 0.9197 0.0865
-4.250 -0.0503 0.04410 0.03573 -0.1181 0.9158 0.0895
-4.000 -0.0159 0.04107 0.03215 -0.1225 0.9096 0.0953
-3.750 0.0267 0.03788 0.02822 -0.1277 0.9056 0.1001
-3.500 0.0655 0.03635 0.02642 -0.1307 0.9019 0.1049
-3.250 0.0943 0.03501 0.02459 -0.1319 0.8950 0.1127
-3.000 0.1276 0.03413 0.02359 -0.1336 0.8896 0.1216
-2.750 0.1677 0.03297 0.02209 -0.1362 0.8859 0.1331
-2.500 0.1912 0.03250 0.02141 -0.1359 0.8773 0.1461
-2.250 0.2277 0.03192 0.02075 -0.1377 0.8723 0.1625
-2.000 0.2534 0.03166 0.02045 -0.1377 0.8639 0.1788
-1.750 0.2892 0.03133 0.02007 -0.1392 0.8580 0.1994
-1.500 0.3168 0.03119 0.01982 -0.1393 0.8495 0.2191
-1.250 0.3527 0.03085 0.01939 -0.1407 0.8433 0.2405
-1.000 0.3798 0.03073 0.01927 -0.1406 0.8349 0.2620
-0.750 0.4150 0.03040 0.01890 -0.1418 0.8286 0.2903
-0.500 0.4418 0.03032 0.01889 -0.1418 0.8203 0.3247
-0.250 0.4754 0.03007 0.01874 -0.1427 0.8140 0.3721
0.000 0.5014 0.03006 0.01882 -0.1424 0.8056 0.4168
0.250 0.5333 0.02987 0.01876 -0.1429 0.7992 0.4711
0.500 0.5581 0.02987 0.01891 -0.1423 0.7907 0.5282
0.750 0.5881 0.02948 0.01881 -0.1422 0.7842 0.6197
1.000 0.6020 0.02879 0.01876 -0.1391 0.7748 1.0000
1.250 0.6379 0.02882 0.01853 -0.1404 0.7687 1.0000
1.500 0.6622 0.02923 0.01876 -0.1399 0.7592 1.0000
1.750 0.6975 0.02920 0.01857 -0.1409 0.7534 1.0000
2.000 0.7199 0.02965 0.01892 -0.1402 0.7435 1.0000
2.250 0.7555 0.02959 0.01876 -0.1411 0.7379 1.0000
2.500 0.7765 0.03010 0.01921 -0.1401 0.7276 1.0000
2.750 0.8126 0.03001 0.01906 -0.1410 0.7223 1.0000
3.000 0.8321 0.03060 0.01963 -0.1399 0.7116 1.0000
3.250 0.8690 0.03047 0.01948 -0.1408 0.7065 1.0000
3.500 0.8867 0.03116 0.02018 -0.1395 0.6955 1.0000
3.750 0.9241 0.03100 0.02002 -0.1404 0.6906 1.0000
4.000 0.9401 0.03181 0.02088 -0.1389 0.6793 1.0000
4.250 0.9782 0.03159 0.02069 -0.1399 0.6747 1.0000
4.500 0.9921 0.03256 0.02172 -0.1381 0.6631 1.0000
4.750 1.0223 0.03274 0.02199 -0.1382 0.6564 1.0000
5.000 1.0430 0.03338 0.02271 -0.1372 0.6469 1.0000
5.250 1.0640 0.03403 0.02345 -0.1362 0.6379 1.0000
5.500 1.0929 0.03427 0.02379 -0.1361 0.6306 1.0000
5.750 1.1086 0.03518 0.02482 -0.1345 0.6203 1.0000
6.000 1.1445 0.03498 0.02476 -0.1351 0.6139 1.0000
6.250 1.1568 0.03594 0.02584 -0.1329 0.6022 1.0000
6.500 1.1841 0.03606 0.02612 -0.1323 0.5929 1.0000
6.750 1.2132 0.03605 0.02627 -0.1319 0.5835 1.0000
7.000 1.2249 0.03703 0.02740 -0.1297 0.5719 1.0000
7.250 1.2541 0.03710 0.02765 -0.1293 0.5632 1.0000
7.500 1.2762 0.03753 0.02831 -0.1281 0.5531 1.0000
7.750 1.2871 0.03859 0.02955 -0.1259 0.5416 1.0000
8.000 1.3090 0.03871 0.02986 -0.1243 0.5288 1.0000
8.250 1.3424 0.03702 0.02825 -0.1226 0.5058 1.0000
8.500 1.3452 0.03728 0.02857 -0.1182 0.4795 1.0000
8.750 1.3506 0.03742 0.02867 -0.1141 0.4489 1.0000
9.000 1.3547 0.03818 0.02944 -0.1106 0.4209 1.0000
9.250 1.3597 0.03919 0.03049 -0.1076 0.3948 1.0000
9.500 1.3592 0.04084 0.03229 -0.1046 0.3689 1.0000
9.750 1.3573 0.04268 0.03421 -0.1017 0.3365 1.0000
10.000 1.3539 0.04472 0.03616 -0.0989 0.2912 1.0000
10.250 1.3464 0.04730 0.03834 -0.0960 0.2392 1.0000
10.500 1.3346 0.05079 0.04151 -0.0936 0.1967 1.0000
10.750 1.3226 0.05470 0.04519 -0.0918 0.1624 1.0000
11.000 1.3117 0.05877 0.04908 -0.0904 0.1393 1.0000
11.250 1.3026 0.06282 0.05301 -0.0893 0.1234 1.0000
11.500 1.2960 0.06672 0.05683 -0.0885 0.1117 1.0000
11.750 1.2903 0.07059 0.06060 -0.0878 0.1031 1.0000
12.000 1.2906 0.07382 0.06395 -0.0870 0.0945 1.0000
12.250 1.2905 0.07711 0.06721 -0.0863 0.0886 1.0000
12.500 1.2944 0.07998 0.07023 -0.0856 0.0820 1.0000
12.750 1.2974 0.08288 0.07307 -0.0849 0.0770 1.0000
13.000 1.3065 0.08520 0.07564 -0.0840 0.0719 1.0000
13.250 1.3136 0.08769 0.07820 -0.0833 0.0673 1.0000
13.500 1.3262 0.08962 0.08026 -0.0820 0.0632 1.0000
13.750 1.3386 0.09180 0.08270 -0.0810 0.0593 1.0000
14.000 1.3507 0.09387 0.08481 -0.0801 0.0557 1.0000
14.250 1.3648 0.09621 0.08734 -0.0791 0.0528 1.0000
14.500 1.3684 0.10001 0.09151 -0.0790 0.0509 1.0000
14.750 1.3675 0.10427 0.09609 -0.0795 0.0492 1.0000
15.000 1.3641 0.10882 0.10089 -0.0805 0.0477 1.0000
15.250 1.3603 0.11339 0.10571 -0.0816 0.0463 1.0000
15.500 1.3576 0.11787 0.11034 -0.0829 0.0451 1.0000
15.750 1.3570 0.12229 0.11488 -0.0840 0.0441 1.0000
16.000 1.3465 0.12845 0.12125 -0.0866 0.0438 1.0000
16.250 1.3295 0.13587 0.12895 -0.0907 0.0437 1.0000
16.500 1.3116 0.14394 0.13726 -0.0955 0.0437 1.0000
16.750 1.2930 0.15273 0.14626 -0.1012 0.0438 1.0000
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