GOE 363 AIRFOIL (goe363-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 363 AIRFOIL (goe363-il) Reynolds number: 50,000 Max Cl/Cd: 32.68 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe363-il-50000.txt Download as CSV file: xf-goe363-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 363 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2630 0.11394 0.10780 -0.0266 1.0000 0.1684
-8.250 -0.2823 0.11429 0.10829 -0.0247 1.0000 0.1712
-8.000 -0.3088 0.11538 0.10955 -0.0221 1.0000 0.1722
-7.750 -0.2941 0.11001 0.10419 -0.0203 1.0000 0.1762
-7.500 -0.2961 0.10786 0.10211 -0.0179 1.0000 0.1808
-7.250 -0.3116 0.10719 0.10155 -0.0152 1.0000 0.1843
-7.000 -0.3362 0.10746 0.10196 -0.0126 1.0000 0.1866
-6.750 -0.3623 0.10821 0.10285 -0.0135 1.0000 0.1882
-6.500 -0.3495 0.10295 0.09763 -0.0095 1.0000 0.1919
-6.250 -0.3501 0.10055 0.09528 -0.0075 1.0000 0.1970
-6.000 -0.3633 0.09961 0.09444 -0.0085 1.0000 0.2026
-5.750 -0.3704 0.09742 0.09233 -0.0098 1.0000 0.2057
-5.500 -0.3647 0.09403 0.08899 -0.0060 1.0000 0.2109
-5.250 -0.3710 0.09329 0.08826 -0.0119 1.0000 0.2201
-5.000 -0.3667 0.08921 0.08428 -0.0069 1.0000 0.2247
-4.750 -0.3641 0.08768 0.08273 -0.0125 1.0000 0.2369
-4.500 -0.3610 0.08413 0.07928 -0.0067 1.0000 0.2432
-4.250 -0.3551 0.08158 0.07673 -0.0094 1.0000 0.2552
-4.000 -0.3458 0.07921 0.07434 -0.0121 1.0000 0.2695
-3.750 -0.3389 0.07660 0.07177 -0.0107 1.0000 0.2816
-3.500 -0.3248 0.07420 0.06932 -0.0145 1.0000 0.3003
-3.250 -0.3163 0.07145 0.06662 -0.0137 1.0000 0.3166
-3.000 -0.3101 0.06888 0.06411 -0.0115 1.0000 0.3352
-2.750 -0.3011 0.06669 0.06195 -0.0109 1.0000 0.3655
-2.500 -0.2951 0.06453 0.05986 -0.0087 1.0000 0.3982
-2.250 -0.2810 0.06214 0.05753 -0.0065 0.9956 0.4470
-2.000 -0.0702 0.05151 0.04487 -0.0613 0.9805 0.2090
-1.750 0.0159 0.04634 0.03847 -0.0741 0.9702 0.1704
-1.500 0.0766 0.04409 0.03553 -0.0812 0.9569 0.1736
-1.250 0.1351 0.04241 0.03350 -0.0872 0.9416 0.1800
-1.000 0.1931 0.04099 0.03166 -0.0925 0.9241 0.1954
-0.750 0.2439 0.03976 0.03011 -0.0962 0.9051 0.2231
-0.500 0.2949 0.03846 0.02879 -0.0994 0.8871 0.2934
-0.250 0.3428 0.03750 0.02800 -0.1023 0.8695 0.3919
0.000 0.3901 0.03653 0.02720 -0.1048 0.8528 0.4587
0.250 0.4334 0.03504 0.02651 -0.1064 0.8370 0.5743
0.500 0.4732 0.03409 0.02573 -0.1064 0.8200 1.0000
0.750 0.5188 0.03394 0.02509 -0.1080 0.8033 1.0000
1.000 0.5629 0.03363 0.02446 -0.1092 0.7868 1.0000
1.250 0.5909 0.03369 0.02432 -0.1084 0.7664 1.0000
1.500 0.6267 0.03329 0.02374 -0.1081 0.7477 1.0000
1.750 0.6649 0.03263 0.02291 -0.1078 0.7297 1.0000
2.000 0.7052 0.03169 0.02182 -0.1075 0.7120 1.0000
2.250 0.7467 0.03055 0.02052 -0.1072 0.6945 1.0000
2.500 0.7740 0.03023 0.02010 -0.1056 0.6709 1.0000
2.750 0.8125 0.02929 0.01900 -0.1051 0.6513 1.0000
3.000 0.8468 0.02872 0.01825 -0.1043 0.6300 1.0000
3.250 0.8773 0.02855 0.01792 -0.1033 0.6076 1.0000
3.500 0.9117 0.02830 0.01744 -0.1028 0.5883 1.0000
3.750 0.9380 0.02881 0.01779 -0.1020 0.5686 1.0000
4.000 0.9637 0.02955 0.01841 -0.1013 0.5514 1.0000
4.250 0.9899 0.03035 0.01912 -0.1008 0.5364 1.0000
4.500 1.0171 0.03112 0.01977 -0.1003 0.5229 1.0000
4.750 1.0421 0.03204 0.02062 -0.0998 0.5102 1.0000
5.000 1.0600 0.03347 0.02215 -0.0987 0.4980 1.0000
5.250 1.0808 0.03478 0.02348 -0.0980 0.4877 1.0000
5.500 1.1114 0.03535 0.02390 -0.0978 0.4774 1.0000
5.750 1.1250 0.03683 0.02550 -0.0963 0.4653 1.0000
6.000 1.1423 0.03800 0.02675 -0.0949 0.4533 1.0000
6.250 1.1648 0.03878 0.02750 -0.0939 0.4418 1.0000
6.500 1.1957 0.03897 0.02753 -0.0936 0.4306 1.0000
6.750 1.2034 0.04086 0.02966 -0.0916 0.4202 1.0000
7.000 1.2215 0.04221 0.03110 -0.0905 0.4113 1.0000
7.250 1.2445 0.04316 0.03207 -0.0897 0.4022 1.0000
7.500 1.2484 0.04557 0.03471 -0.0876 0.3936 1.0000
7.750 1.2836 0.04585 0.03490 -0.0878 0.3853 1.0000
8.000 1.2675 0.04982 0.03927 -0.0843 0.3776 1.0000
8.250 1.3113 0.04967 0.03898 -0.0851 0.3698 1.0000
8.500 1.2654 0.05597 0.04577 -0.0799 0.3634 1.0000
8.750 1.3001 0.05646 0.04625 -0.0800 0.3560 1.0000
9.000 1.2298 0.06513 0.05522 -0.0747 0.3519 1.0000
9.250 0.7927 0.13328 0.12349 -0.1038 0.4824 1.0000
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Polar data table (+)
Polar graphs
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