GOE 490 AIRFOIL (goe490-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 490 AIRFOIL (goe490-il) Reynolds number: 50,000 Max Cl/Cd: 33.18 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe490-il-50000.txt Download as CSV file: xf-goe490-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 490 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3584 0.11741 0.11024 -0.0226 1.0000 0.1703
-9.250 -0.3662 0.11629 0.10923 -0.0237 1.0000 0.1753
-9.000 -0.3739 0.11444 0.10750 -0.0246 1.0000 0.1775
-8.750 -0.3531 0.10892 0.10195 -0.0228 1.0000 0.1843
-8.500 -0.3625 0.10778 0.10093 -0.0234 1.0000 0.1900
-8.250 -0.3587 0.10412 0.09734 -0.0229 1.0000 0.1944
-8.000 -0.3573 0.10165 0.09493 -0.0221 1.0000 0.2033
-7.750 -0.3815 0.10181 0.09529 -0.0220 1.0000 0.2058
-7.500 -0.3588 0.09638 0.08984 -0.0203 1.0000 0.2168
-7.250 -0.3856 0.09647 0.09014 -0.0197 1.0000 0.2203
-7.000 -0.3672 0.09154 0.08518 -0.0174 1.0000 0.2290
-6.750 -0.3904 0.09120 0.08505 -0.0178 1.0000 0.2351
-6.500 -0.3776 0.08677 0.08063 -0.0150 1.0000 0.2420
-6.250 -0.3968 0.08617 0.08016 -0.0160 1.0000 0.2502
-6.000 -0.3855 0.08191 0.07595 -0.0125 1.0000 0.2576
-5.750 -0.3999 0.08056 0.07469 -0.0134 1.0000 0.2664
-5.500 -0.3993 0.07795 0.07214 -0.0113 1.0000 0.2790
-5.250 -0.3977 0.07501 0.06926 -0.0087 1.0000 0.2922
-5.000 -0.3988 0.07245 0.06675 -0.0069 1.0000 0.3063
-4.750 -0.4031 0.07030 0.06464 -0.0065 1.0000 0.3238
-4.500 -0.4005 0.06724 0.06164 -0.0033 1.0000 0.3399
-4.250 -0.3980 0.06449 0.05895 -0.0002 1.0000 0.3579
-4.000 -0.3988 0.06209 0.05659 0.0024 1.0000 0.3852
-3.750 -0.3989 0.05968 0.05423 0.0065 1.0000 0.4160
-3.000 -0.2711 0.04373 0.03617 -0.0270 1.0000 0.1938
-2.750 -0.2429 0.03992 0.03165 -0.0285 1.0000 0.1753
-2.500 -0.2215 0.03752 0.02895 -0.0283 1.0000 0.1734
-2.250 -0.1982 0.03548 0.02631 -0.0282 1.0000 0.1765
-2.000 -0.1790 0.03390 0.02464 -0.0275 1.0000 0.1807
-1.750 -0.1575 0.03238 0.02277 -0.0269 1.0000 0.1842
-1.500 -0.1350 0.03101 0.02093 -0.0263 1.0000 0.1901
-1.250 -0.1156 0.03025 0.02005 -0.0255 1.0000 0.2038
-1.000 -0.0948 0.02955 0.01918 -0.0249 1.0000 0.2220
-0.750 -0.0758 0.02892 0.01852 -0.0240 1.0000 0.2447
-0.500 -0.0576 0.02852 0.01798 -0.0230 1.0000 0.2810
-0.250 -0.0344 0.02805 0.01751 -0.0232 1.0000 0.3276
0.000 0.0102 0.02766 0.01722 -0.0273 0.9932 0.3895
0.250 0.0676 0.02719 0.01727 -0.0336 0.9785 0.4787
0.500 0.1472 0.02641 0.01733 -0.0437 0.9625 1.0000
0.750 0.2038 0.02745 0.01787 -0.0498 0.9445 1.0000
1.000 0.2483 0.02819 0.01834 -0.0537 0.9244 1.0000
1.250 0.2962 0.02887 0.01882 -0.0580 0.9051 1.0000
1.500 0.3473 0.02945 0.01923 -0.0626 0.8869 1.0000
1.750 0.3850 0.02996 0.01964 -0.0647 0.8665 1.0000
2.000 0.4268 0.03036 0.01997 -0.0673 0.8474 1.0000
2.250 0.4747 0.03054 0.02009 -0.0704 0.8295 1.0000
2.500 0.5278 0.03039 0.01993 -0.0740 0.8126 1.0000
2.750 0.5602 0.03061 0.02016 -0.0744 0.7923 1.0000
3.000 0.6038 0.03043 0.01999 -0.0761 0.7741 1.0000
3.250 0.6490 0.03003 0.01963 -0.0777 0.7567 1.0000
3.500 0.6945 0.02951 0.01917 -0.0790 0.7398 1.0000
3.750 0.7283 0.02940 0.01910 -0.0787 0.7212 1.0000
4.000 0.7563 0.02952 0.01929 -0.0778 0.7014 1.0000
4.250 0.7931 0.02919 0.01901 -0.0776 0.6826 1.0000
4.500 0.8316 0.02875 0.01859 -0.0775 0.6637 1.0000
4.750 0.8520 0.02917 0.01906 -0.0755 0.6413 1.0000
5.000 0.8890 0.02872 0.01864 -0.0750 0.6202 1.0000
5.250 0.9086 0.02918 0.01915 -0.0727 0.5966 1.0000
5.500 0.9400 0.02905 0.01899 -0.0717 0.5739 1.0000
5.750 0.9606 0.02955 0.01956 -0.0696 0.5502 1.0000
6.000 0.9859 0.02993 0.01993 -0.0681 0.5279 1.0000
6.250 1.0078 0.03056 0.02059 -0.0664 0.5057 1.0000
6.500 1.0334 0.03115 0.02116 -0.0652 0.4854 1.0000
6.750 1.0504 0.03227 0.02242 -0.0632 0.4656 1.0000
7.000 1.0717 0.03327 0.02348 -0.0617 0.4473 1.0000
7.250 1.0925 0.03444 0.02473 -0.0603 0.4310 1.0000
7.500 1.1099 0.03595 0.02640 -0.0587 0.4168 1.0000
7.750 1.1245 0.03771 0.02837 -0.0568 0.4042 1.0000
8.000 1.1402 0.03944 0.03032 -0.0552 0.3927 1.0000
8.250 1.1587 0.04068 0.03170 -0.0536 0.3796 1.0000
8.500 1.1750 0.04155 0.03270 -0.0515 0.3640 1.0000
8.750 1.1936 0.04152 0.03275 -0.0493 0.3447 1.0000
9.000 1.2111 0.04208 0.03345 -0.0473 0.3299 1.0000
9.250 1.2414 0.04084 0.03214 -0.0460 0.3094 1.0000
9.500 1.2472 0.04081 0.03232 -0.0423 0.2895 1.0000
9.750 1.2538 0.03918 0.03057 -0.0381 0.2613 1.0000
10.000 1.2534 0.03866 0.02998 -0.0334 0.2360 1.0000
10.250 1.2437 0.03920 0.03061 -0.0281 0.2115 1.0000
10.500 1.2264 0.04041 0.03184 -0.0222 0.1858 1.0000
10.750 1.2080 0.04237 0.03368 -0.0170 0.1594 1.0000
11.000 1.1923 0.04503 0.03609 -0.0131 0.1359 1.0000
11.250 1.1848 0.04794 0.03890 -0.0103 0.1189 1.0000
11.500 1.1834 0.05078 0.04171 -0.0083 0.1073 1.0000
11.750 1.1852 0.05339 0.04420 -0.0066 0.0987 1.0000
12.000 1.1863 0.05641 0.04752 -0.0052 0.0922 1.0000
12.250 1.1905 0.05902 0.05005 -0.0040 0.0865 1.0000
12.500 1.1895 0.06260 0.05397 -0.0030 0.0829 1.0000
12.750 1.1909 0.06607 0.05764 -0.0021 0.0799 1.0000
13.000 1.1942 0.06948 0.06119 -0.0015 0.0780 1.0000
13.250 1.2021 0.07310 0.06485 -0.0007 0.0761 1.0000
13.500 1.1872 0.07823 0.07030 -0.0011 0.0759 1.0000
13.750 1.1689 0.08393 0.07626 -0.0024 0.0759 1.0000
14.000 1.1494 0.09008 0.08264 -0.0044 0.0762 1.0000
14.250 0.9830 0.12727 0.12038 -0.0306 0.0966 1.0000
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Polar data table (+)
Polar graphs
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