GOE 396 AIRFOIL (goe396-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: GOE 396 AIRFOIL (goe396-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.82 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe396-il-1000000-n5.txt Download as CSV file: xf-goe396-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 396 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2424 0.12092 0.11938 -0.0319 1.0000 0.0026
-11.250 -0.2388 0.11803 0.11650 -0.0323 1.0000 0.0026
-11.000 -0.2351 0.11518 0.11366 -0.0326 1.0000 0.0026
-10.750 -0.2273 0.11153 0.11002 -0.0344 0.9985 0.0026
-10.500 -0.2203 0.10806 0.10655 -0.0359 0.9933 0.0026
-10.250 -0.2118 0.10437 0.10285 -0.0378 0.9895 0.0026
-10.000 -0.2030 0.10057 0.09905 -0.0399 0.9850 0.0026
-9.750 -0.1928 0.09659 0.09507 -0.0424 0.9801 0.0026
-9.500 -0.1811 0.09254 0.09101 -0.0453 0.9747 0.0026
-9.000 -0.1547 0.08313 0.08158 -0.0524 0.9589 0.0028
-8.750 -0.1380 0.07868 0.07709 -0.0567 0.9472 0.0029
-8.250 -0.1109 0.07077 0.06900 -0.0632 0.9009 0.0030
-8.000 -0.1059 0.06774 0.06588 -0.0639 0.8772 0.0029
-7.750 -0.1015 0.06498 0.06305 -0.0643 0.8595 0.0030
-7.500 -0.0973 0.06222 0.06024 -0.0647 0.8466 0.0031
-6.500 -0.1045 0.06807 0.06597 -0.0783 0.8433 0.0027
-6.250 -0.0924 0.06557 0.06341 -0.0801 0.8322 0.0025
-6.000 -0.0781 0.06252 0.06032 -0.0829 0.8232 0.0025
-5.750 -0.0620 0.05953 0.05728 -0.0857 0.8152 0.0024
-5.500 -0.0424 0.05564 0.05335 -0.0895 0.8078 0.0025
-5.250 -0.0211 0.05210 0.04975 -0.0932 0.8015 0.0025
-5.000 0.0029 0.04797 0.04557 -0.0976 0.7947 0.0028
-4.750 0.0273 0.04517 0.04270 -0.1007 0.7880 0.0030
-4.500 0.0526 0.04276 0.04021 -0.1033 0.7806 0.0038
-4.250 0.0814 0.03880 0.03614 -0.1071 0.7719 0.0036
-4.000 0.1117 0.03481 0.03201 -0.1105 0.7644 0.0038
-3.500 0.1769 0.01154 0.00707 -0.1179 0.7563 0.0030
-3.250 0.2021 0.01012 0.00524 -0.1173 0.7455 0.0030
-3.000 0.2280 0.00925 0.00410 -0.1168 0.7357 0.0032
-2.750 0.2543 0.00865 0.00329 -0.1164 0.7268 0.0034
-2.500 0.2806 0.00820 0.00267 -0.1160 0.7172 0.0041
-2.250 0.3071 0.00792 0.00225 -0.1156 0.7061 0.0046
-2.000 0.3333 0.00756 0.00177 -0.1152 0.6940 0.0059
-1.750 0.3592 0.00746 0.00154 -0.1148 0.6771 0.0077
-1.500 0.3851 0.00727 0.00123 -0.1142 0.6606 0.0121
-1.250 0.4112 0.00721 0.00114 -0.1139 0.6468 0.0234
-1.000 0.4375 0.00722 0.00105 -0.1136 0.6330 0.0255
-0.500 0.4900 0.00718 0.00088 -0.1129 0.6072 0.0350
-0.250 0.5163 0.00715 0.00081 -0.1126 0.5948 0.0415
0.000 0.5424 0.00714 0.00076 -0.1123 0.5818 0.0533
0.250 0.5684 0.00711 0.00076 -0.1119 0.5689 0.0845
0.500 0.5947 0.00715 0.00077 -0.1116 0.5564 0.0987
0.750 0.6208 0.00720 0.00078 -0.1113 0.5424 0.1085
1.000 0.6465 0.00729 0.00082 -0.1110 0.5232 0.1193
1.500 0.6978 0.00749 0.00092 -0.1102 0.4847 0.1407
1.750 0.7227 0.00760 0.00102 -0.1097 0.4611 0.1731
2.000 0.7476 0.00776 0.00112 -0.1093 0.4354 0.1966
2.250 0.7727 0.00789 0.00123 -0.1088 0.4138 0.2241
2.500 0.7973 0.00806 0.00138 -0.1083 0.3892 0.2614
2.750 0.8215 0.00823 0.00155 -0.1078 0.3615 0.3141
3.000 0.8445 0.00848 0.00177 -0.1070 0.3222 0.3843
3.250 0.8781 0.00893 0.00259 -0.1100 0.1385 1.0000
3.500 0.9017 0.00925 0.00283 -0.1093 0.1185 1.0000
3.750 0.9259 0.00949 0.00303 -0.1087 0.1074 1.0000
4.000 0.9499 0.00975 0.00323 -0.1081 0.0950 1.0000
4.250 0.9683 0.01058 0.00371 -0.1065 0.0144 1.0000
4.500 0.9922 0.01086 0.00402 -0.1058 0.0084 1.0000
4.750 1.0158 0.01117 0.00437 -0.1050 0.0057 1.0000
5.000 1.0388 0.01152 0.00475 -0.1041 0.0045 1.0000
5.250 1.0610 0.01197 0.00527 -0.1031 0.0038 1.0000
5.500 1.0841 0.01228 0.00560 -0.1023 0.0030 1.0000
5.750 1.1052 0.01280 0.00617 -0.1012 0.0025 1.0000
6.000 1.1255 0.01340 0.00687 -0.0998 0.0022 1.0000
6.250 1.1450 0.01407 0.00762 -0.0983 0.0019 1.0000
6.500 1.1625 0.01490 0.00855 -0.0964 0.0018 1.0000
6.750 1.1780 0.01590 0.00966 -0.0942 0.0017 1.0000
7.000 1.1914 0.01709 0.01099 -0.0916 0.0016 1.0000
7.250 1.2041 0.01845 0.01246 -0.0889 0.0016 1.0000
7.500 1.2193 0.01963 0.01373 -0.0868 0.0015 1.0000
7.750 1.2393 0.01995 0.01409 -0.0859 0.0013 1.0000
8.000 1.2518 0.02181 0.01610 -0.0834 0.0012 1.0000
8.250 1.2687 0.02367 0.01811 -0.0815 0.0011 1.0000
8.500 1.2901 0.02674 0.02141 -0.0800 0.0010 1.0000
8.750 1.3098 0.03015 0.02509 -0.0783 0.0008 1.0000
9.000 1.3238 0.03322 0.02844 -0.0760 0.0007 1.0000
9.250 1.3333 0.03612 0.03162 -0.0732 0.0006 1.0000
9.500 1.3375 0.03971 0.03553 -0.0697 0.0006 1.0000
9.750 1.3380 0.04318 0.03928 -0.0660 0.0006 1.0000
10.000 1.3328 0.04672 0.04310 -0.0618 0.0006 1.0000
10.250 1.3206 0.04984 0.04644 -0.0567 0.0006 1.0000
10.500 1.3057 0.05291 0.04972 -0.0520 0.0007 1.0000
10.750 1.2882 0.05628 0.05329 -0.0480 0.0007 1.0000
11.000 1.2722 0.05964 0.05683 -0.0452 0.0007 1.0000
11.250 1.2530 0.06375 0.06111 -0.0431 0.0007 1.0000
11.500 1.2347 0.06804 0.06556 -0.0421 0.0007 1.0000
11.750 1.2156 0.07283 0.07050 -0.0420 0.0007 1.0000
12.000 1.1957 0.07818 0.07600 -0.0429 0.0007 1.0000
12.250 1.1769 0.08391 0.08186 -0.0447 0.0007 1.0000
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Polar data table (+)
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