GOE 443 AIRFOIL (goe443-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 443 AIRFOIL (goe443-il) Reynolds number: 1,000,000 Max Cl/Cd: 43.28 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe443-il-1000000.txt Download as CSV file: xf-goe443-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 443 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6353 0.08425 0.08265 0.0024 1.0000 0.0070
-8.000 -0.6408 0.07973 0.07816 -0.0016 1.0000 0.0070
-7.750 -0.6429 0.07500 0.07341 -0.0055 1.0000 0.0070
-7.500 -0.6396 0.07021 0.06857 -0.0086 1.0000 0.0070
-7.250 -0.6339 0.06567 0.06396 -0.0107 1.0000 0.0071
-7.000 -0.6269 0.06120 0.05940 -0.0120 1.0000 0.0071
-6.750 -0.6179 0.05688 0.05497 -0.0128 1.0000 0.0071
-6.500 -0.6073 0.05263 0.05059 -0.0131 1.0000 0.0072
-6.250 -0.5952 0.04843 0.04625 -0.0130 1.0000 0.0072
-6.000 -0.5818 0.04440 0.04205 -0.0125 1.0000 0.0072
-5.750 -0.5674 0.04043 0.03789 -0.0116 1.0000 0.0072
-5.500 -0.5520 0.03666 0.03391 -0.0104 1.0000 0.0072
-5.250 -0.5360 0.03296 0.02998 -0.0090 1.0000 0.0072
-5.000 -0.5195 0.02942 0.02619 -0.0073 1.0000 0.0073
-4.750 -0.5122 0.02179 0.01795 -0.0040 1.0000 0.0060
-4.500 -0.4949 0.01659 0.01217 -0.0008 1.0000 0.0053
-4.250 -0.4724 0.01469 0.01003 0.0008 1.0000 0.0063
-4.000 -0.4471 0.01505 0.01037 0.0014 1.0000 0.0075
-3.750 -0.4273 0.01182 0.00678 0.0033 1.0000 0.0081
-3.500 -0.4048 0.01095 0.00582 0.0043 1.0000 0.0100
-3.250 -0.3840 0.00940 0.00410 0.0061 1.0000 0.0091
-3.000 -0.3622 0.00856 0.00315 0.0076 1.0000 0.0090
-2.750 -0.3399 0.00784 0.00232 0.0089 1.0000 0.0101
-2.500 -0.3163 0.00750 0.00194 0.0098 1.0000 0.0132
-2.250 -0.2924 0.00729 0.00170 0.0107 1.0000 0.0151
-2.000 -0.2692 0.00689 0.00131 0.0117 1.0000 0.0350
-1.750 -0.2427 0.00670 0.00114 0.0119 0.9996 0.0522
-1.500 -0.2101 0.00602 0.00097 0.0103 0.9974 0.2034
-1.250 -0.1812 0.00479 0.00085 0.0091 0.9946 0.5222
-1.000 -0.1528 0.00412 0.00081 0.0087 0.9908 0.7037
-0.750 -0.1234 0.00371 0.00081 0.0084 0.9864 0.8151
-0.500 -0.0914 0.00346 0.00082 0.0076 0.9831 0.8863
-0.250 -0.0489 0.00344 0.00097 0.0047 0.9837 0.9631
0.000 -0.0001 0.00354 0.00108 0.0000 0.9851 0.9851
0.250 0.0489 0.00344 0.00097 -0.0047 0.9636 0.9838
0.500 0.0914 0.00346 0.00082 -0.0076 0.8863 0.9831
0.750 0.1235 0.00371 0.00081 -0.0084 0.8160 0.9865
1.000 0.1537 0.00405 0.00082 -0.0089 0.7230 0.9908
1.250 0.1813 0.00479 0.00084 -0.0092 0.5220 0.9947
1.500 0.2105 0.00597 0.00096 -0.0104 0.2164 0.9975
1.750 0.2429 0.00670 0.00113 -0.0119 0.0519 0.9997
2.000 0.2686 0.00688 0.00131 -0.0116 0.0357 1.0000
2.250 0.2918 0.00728 0.00169 -0.0105 0.0151 1.0000
2.500 0.3157 0.00750 0.00194 -0.0097 0.0134 1.0000
2.750 0.3393 0.00784 0.00232 -0.0087 0.0100 1.0000
3.000 0.3615 0.00854 0.00314 -0.0074 0.0090 1.0000
3.250 0.3833 0.00938 0.00409 -0.0060 0.0091 1.0000
3.500 0.4042 0.01091 0.00578 -0.0042 0.0100 1.0000
3.750 0.4268 0.01173 0.00668 -0.0032 0.0081 1.0000
4.000 0.4467 0.01484 0.01013 -0.0013 0.0075 1.0000
4.250 0.4715 0.01478 0.01013 -0.0006 0.0064 1.0000
4.500 0.4943 0.01655 0.01213 0.0009 0.0053 1.0000
4.750 0.5118 0.02176 0.01792 0.0041 0.0060 1.0000
15.500 0.7548 0.19955 0.19781 -0.0540 0.0031 1.0000
15.750 0.7620 0.20332 0.20156 -0.0559 0.0030 1.0000
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Polar data table (+)
Polar graphs
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