GOE 559 AIRFOIL (goe559-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 559 AIRFOIL (goe559-il) Reynolds number: 50,000 Max Cl/Cd: 30.09 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe559-il-50000.txt Download as CSV file: xf-goe559-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 559 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3615 0.11249 0.10646 -0.0307 1.0000 0.1845
-9.000 -0.3592 0.10948 0.10353 -0.0305 1.0000 0.1988
-8.750 -0.3737 0.10855 0.10274 -0.0321 1.0000 0.2045
-8.500 -0.3583 0.10414 0.09836 -0.0297 1.0000 0.2306
-8.250 -0.3629 0.10204 0.09638 -0.0292 1.0000 0.2466
-8.000 -0.3573 0.09894 0.09337 -0.0271 1.0000 0.2747
-7.750 -0.3504 0.09613 0.09062 -0.0248 1.0000 0.3029
-7.500 -0.3552 0.09414 0.08876 -0.0223 1.0000 0.3331
-7.250 -0.3295 0.08999 0.08462 -0.0181 1.0000 0.3876
-7.000 -0.3213 0.08738 0.08209 -0.0147 1.0000 0.4319
-6.750 -0.3184 0.08516 0.07993 -0.0107 1.0000 0.4768
-6.500 -0.2984 0.08183 0.07665 -0.0071 1.0000 0.5343
-6.250 -0.2561 0.07633 0.07110 -0.0046 1.0000 0.6188
-5.750 -0.2008 0.06792 0.06276 -0.0038 1.0000 0.7251
-5.500 -0.1833 0.06443 0.05931 -0.0040 1.0000 0.7550
-4.250 -0.2343 0.05863 0.05442 0.0119 1.0000 0.7822
-4.000 -0.2680 0.06009 0.05611 0.0184 1.0000 0.7878
-3.750 -0.3124 0.05905 0.05522 0.0090 0.9626 0.6688
-3.500 -0.2801 0.04601 0.04085 -0.0507 0.9222 0.3450
-3.250 -0.2095 0.04007 0.03317 -0.0630 0.9092 0.2271
-3.000 -0.1547 0.03755 0.02941 -0.0663 0.8965 0.1736
-2.750 -0.1039 0.03545 0.02652 -0.0684 0.8847 0.1406
-2.500 -0.0509 0.03384 0.02412 -0.0706 0.8739 0.1163
-2.250 0.0053 0.03200 0.02185 -0.0734 0.8648 0.0992
-2.000 0.0467 0.03099 0.02050 -0.0742 0.8531 0.0890
-1.750 0.0852 0.02996 0.01926 -0.0751 0.8418 0.0847
-1.500 0.1165 0.02919 0.01817 -0.0751 0.8308 0.0851
-1.250 0.1525 0.02848 0.01710 -0.0760 0.8217 0.0880
-1.000 0.1827 0.02816 0.01649 -0.0762 0.8115 0.0927
-0.750 0.2060 0.02792 0.01621 -0.0756 0.8009 0.1160
-0.500 0.3255 0.02452 0.01459 -0.0901 0.7962 1.0000
-0.250 0.3401 0.02528 0.01496 -0.0884 0.7853 1.0000
0.000 0.3581 0.02599 0.01531 -0.0874 0.7762 1.0000
0.250 0.3852 0.02639 0.01537 -0.0875 0.7687 1.0000
0.500 0.3944 0.02750 0.01627 -0.0855 0.7594 1.0000
0.750 0.4260 0.02779 0.01630 -0.0862 0.7533 1.0000
1.000 0.4285 0.02926 0.01770 -0.0835 0.7443 1.0000
1.250 0.4570 0.02977 0.01809 -0.0840 0.7391 1.0000
1.500 0.4529 0.03165 0.01994 -0.0808 0.7312 1.0000
1.750 0.4815 0.03223 0.02050 -0.0813 0.7262 1.0000
2.000 0.4741 0.03437 0.02266 -0.0779 0.7190 1.0000
2.250 0.4896 0.03561 0.02393 -0.0772 0.7141 1.0000
2.500 0.5055 0.03695 0.02532 -0.0766 0.7101 1.0000
2.750 0.4864 0.03976 0.02809 -0.0725 0.7054 1.0000
3.000 0.4886 0.04162 0.03001 -0.0705 0.7015 1.0000
3.250 0.5089 0.04291 0.03144 -0.0706 0.6982 1.0000
3.500 0.5140 0.04491 0.03359 -0.0692 0.6966 1.0000
3.750 0.5052 0.04736 0.03608 -0.0666 0.6958 1.0000
4.000 0.6836 0.02272 0.01003 -0.0496 0.2808 1.0000
4.250 0.6813 0.02550 0.01175 -0.0460 0.0780 1.0000
4.500 0.6964 0.02671 0.01316 -0.0439 0.0703 1.0000
4.750 0.7111 0.02780 0.01454 -0.0419 0.0695 1.0000
5.000 0.7239 0.02900 0.01603 -0.0396 0.0699 1.0000
5.250 0.7346 0.03026 0.01761 -0.0372 0.0715 1.0000
5.500 0.7416 0.03172 0.01934 -0.0344 0.0735 1.0000
5.750 0.7440 0.03332 0.02118 -0.0312 0.0755 1.0000
6.000 0.7429 0.03506 0.02307 -0.0280 0.0769 1.0000
6.250 0.7382 0.03719 0.02535 -0.0250 0.0784 1.0000
6.500 0.7461 0.03860 0.02703 -0.0230 0.0810 1.0000
6.750 0.7529 0.04019 0.02882 -0.0208 0.0851 1.0000
7.000 0.7594 0.04185 0.03056 -0.0184 0.0888 1.0000
7.250 0.7812 0.04244 0.03127 -0.0156 0.0939 1.0000
7.500 0.9674 0.03975 0.02899 -0.0208 0.1332 1.0000
7.750 1.0720 0.04061 0.03059 -0.0247 0.1731 1.0000
8.000 1.1217 0.04221 0.03322 -0.0242 0.2026 1.0000
8.750 1.0784 0.03947 0.03324 -0.0118 0.2420 1.0000
9.000 1.0503 0.04426 0.03840 -0.0080 0.2432 1.0000
9.250 1.0209 0.04903 0.04339 -0.0047 0.2432 1.0000
9.500 0.9915 0.05372 0.04817 -0.0018 0.2424 1.0000
9.750 0.9635 0.05904 0.05355 -0.0003 0.2414 1.0000
10.000 0.9157 0.06351 0.05802 0.0010 0.2296 1.0000
10.250 0.8719 0.06973 0.06422 0.0003 0.2196 1.0000
10.500 0.8424 0.07662 0.07110 -0.0012 0.2158 1.0000
10.750 0.8001 0.08425 0.07867 -0.0038 0.2063 1.0000
11.000 0.7692 0.09216 0.08654 -0.0068 0.2028 1.0000
11.250 0.7415 0.10004 0.09437 -0.0100 0.2016 1.0000
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Polar data table (+)
Polar graphs
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