GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 623 AIRFOIL (goe623-il) Reynolds number: 50,000 Max Cl/Cd: 27.38 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe623-il-50000.txt Download as CSV file: xf-goe623-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 623 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3361 0.10670 0.09983 -0.0257 1.0000 0.2500
-8.500 -0.3327 0.10343 0.09663 -0.0254 1.0000 0.2576
-8.250 -0.3452 0.10229 0.09562 -0.0253 1.0000 0.2680
-8.000 -0.3275 0.09795 0.09130 -0.0240 1.0000 0.2773
-7.750 -0.3635 0.09853 0.09213 -0.0227 1.0000 0.2850
-7.500 -0.3349 0.09344 0.08700 -0.0213 1.0000 0.2962
-7.250 -0.3868 0.09502 0.08889 -0.0175 1.0000 0.3015
-7.000 -0.3593 0.09029 0.08413 -0.0158 1.0000 0.3149
-6.750 -0.3689 0.08823 0.08220 -0.0126 1.0000 0.3227
-6.500 -0.3986 0.08805 0.08219 -0.0087 1.0000 0.3329
-6.250 -0.3925 0.08519 0.07938 -0.0055 1.0000 0.3458
-6.000 -0.4005 0.08329 0.07757 -0.0021 1.0000 0.3593
-5.750 -0.4103 0.08155 0.07594 0.0014 1.0000 0.3749
-5.500 -0.4188 0.07982 0.07429 0.0050 1.0000 0.3928
-5.250 -0.4320 0.07840 0.07297 0.0086 1.0000 0.4130
-4.750 -0.4200 0.05376 0.04677 -0.0349 1.0000 0.1747
-4.500 -0.4034 0.05033 0.04315 -0.0353 1.0000 0.1680
-4.250 -0.3770 0.04505 0.03688 -0.0387 1.0000 0.1567
-4.000 -0.3550 0.04227 0.03368 -0.0395 1.0000 0.1564
-3.750 -0.3334 0.04001 0.03112 -0.0400 1.0000 0.1595
-3.500 -0.3125 0.03841 0.02934 -0.0401 1.0000 0.1635
-3.250 -0.2888 0.03668 0.02721 -0.0405 1.0000 0.1668
-3.000 -0.2637 0.03518 0.02516 -0.0409 1.0000 0.1723
-2.750 -0.2425 0.03415 0.02413 -0.0409 1.0000 0.1824
-2.500 -0.2192 0.03317 0.02294 -0.0410 1.0000 0.1955
-2.250 -0.1956 0.03228 0.02195 -0.0410 1.0000 0.2145
-2.000 -0.1486 0.03132 0.02107 -0.0449 0.9926 0.2718
-1.750 -0.1048 0.03082 0.02091 -0.0485 0.9846 0.3598
-1.500 -0.0645 0.03037 0.02080 -0.0514 0.9761 0.4448
-1.250 -0.0236 0.02938 0.02086 -0.0536 0.9690 0.5984
-1.000 0.0116 0.02866 0.02062 -0.0540 0.9587 1.0000
-0.750 0.0462 0.02945 0.02091 -0.0565 0.9484 1.0000
-0.500 0.0850 0.03036 0.02140 -0.0596 0.9391 1.0000
-0.250 0.1204 0.03120 0.02194 -0.0621 0.9290 1.0000
0.000 0.1489 0.03202 0.02252 -0.0634 0.9187 1.0000
0.250 0.1875 0.03294 0.02319 -0.0663 0.9091 1.0000
0.500 0.2165 0.03377 0.02384 -0.0675 0.8983 1.0000
0.750 0.2433 0.03464 0.02456 -0.0684 0.8873 1.0000
1.000 0.2800 0.03553 0.02528 -0.0707 0.8766 1.0000
1.250 0.3123 0.03636 0.02599 -0.0723 0.8650 1.0000
1.500 0.3355 0.03724 0.02678 -0.0724 0.8526 1.0000
1.750 0.3642 0.03811 0.02756 -0.0733 0.8403 1.0000
2.000 0.3988 0.03890 0.02828 -0.0749 0.8279 1.0000
2.250 0.4398 0.03952 0.02884 -0.0771 0.8154 1.0000
2.500 0.4631 0.04033 0.02962 -0.0769 0.8011 1.0000
2.750 0.4895 0.04108 0.03034 -0.0770 0.7864 1.0000
3.000 0.5184 0.04172 0.03097 -0.0772 0.7713 1.0000
3.250 0.5493 0.04222 0.03148 -0.0775 0.7558 1.0000
3.500 0.5819 0.04258 0.03184 -0.0778 0.7399 1.0000
3.750 0.6164 0.04273 0.03203 -0.0780 0.7239 1.0000
4.000 0.6527 0.04266 0.03200 -0.0782 0.7079 1.0000
4.250 0.6910 0.04233 0.03174 -0.0783 0.6920 1.0000
4.500 0.7285 0.04183 0.03130 -0.0779 0.6762 1.0000
4.750 0.7653 0.04119 0.03072 -0.0773 0.6605 1.0000
5.000 0.8020 0.04042 0.03003 -0.0764 0.6446 1.0000
5.250 0.8390 0.03959 0.02926 -0.0755 0.6286 1.0000
5.500 0.8775 0.03858 0.02834 -0.0747 0.6124 1.0000
6.000 0.9246 0.03893 0.02881 -0.0712 0.5731 1.0000
6.250 0.9563 0.03856 0.02850 -0.0701 0.5550 1.0000
6.500 0.9881 0.03828 0.02827 -0.0691 0.5373 1.0000
6.750 1.0185 0.03818 0.02820 -0.0681 0.5201 1.0000
7.000 1.0462 0.03836 0.02842 -0.0671 0.5035 1.0000
7.250 1.0690 0.03904 0.02916 -0.0658 0.4878 1.0000
7.500 1.0855 0.04034 0.03057 -0.0644 0.4734 1.0000
7.750 1.0982 0.04199 0.03234 -0.0628 0.4601 1.0000
8.000 1.1112 0.04367 0.03416 -0.0613 0.4482 1.0000
8.250 1.1446 0.04384 0.03436 -0.0610 0.4381 1.0000
8.500 1.1399 0.04711 0.03784 -0.0587 0.4281 1.0000
8.750 1.1355 0.05061 0.04150 -0.0567 0.4201 1.0000
9.000 1.1296 0.05423 0.04526 -0.0548 0.4122 1.0000
9.250 0.9451 0.07938 0.07011 -0.0565 0.4053 1.0000
9.500 0.9003 0.08942 0.08010 -0.0590 0.4020 1.0000
9.750 0.8843 0.09577 0.08646 -0.0604 0.3998 1.0000
10.000 0.8624 0.10313 0.09384 -0.0626 0.4027 1.0000
10.250 0.8591 0.10875 0.09952 -0.0642 0.4067 1.0000
10.500 0.8693 0.11318 0.10406 -0.0653 0.4090 1.0000
12.000 1.3937 0.05574 0.04813 -0.0366 0.2562 1.0000
12.250 1.3544 0.06038 0.05309 -0.0319 0.2536 1.0000
12.500 1.3089 0.06710 0.06004 -0.0293 0.2539 1.0000
12.750 1.2563 0.07665 0.06970 -0.0295 0.2567 1.0000
13.000 1.2442 0.07928 0.07241 -0.0279 0.2409 1.0000
13.250 1.3253 0.06532 0.05764 -0.0196 0.1654 1.0000
13.500 1.3146 0.06837 0.06065 -0.0181 0.1525 1.0000
13.750 1.2855 0.07447 0.06706 -0.0181 0.1489 1.0000
14.000 1.2806 0.07759 0.07012 -0.0174 0.1385 1.0000
14.250 1.2481 0.08514 0.07796 -0.0190 0.1377 1.0000
14.500 1.2095 0.09446 0.08751 -0.0222 0.1389 1.0000
14.750 1.1685 0.10531 0.09847 -0.0267 0.1407 1.0000
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Polar data table (+)
Polar graphs
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