GOE 370 AIRFOIL (goe370-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 370 AIRFOIL (goe370-il) Reynolds number: 200,000 Max Cl/Cd: 92.25 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe370-il-200000-n5.txt Download as CSV file: xf-goe370-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 370 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3182 0.12235 0.11874 -0.0310 1.0000 0.0142
-9.250 -0.2313 0.10392 0.10074 -0.0352 1.0000 0.0143
-7.250 -0.2862 0.09300 0.08985 -0.0336 0.9925 0.0152
-7.000 -0.2690 0.08913 0.08597 -0.0351 0.9883 0.0168
-6.750 -0.2476 0.08539 0.08223 -0.0400 0.9800 0.0182
-6.500 -0.2257 0.08161 0.07844 -0.0454 0.9709 0.0194
-6.250 -0.2023 0.07769 0.07448 -0.0511 0.9613 0.0208
-6.000 -0.1721 0.07378 0.07054 -0.0586 0.9524 0.0239
-5.750 -0.1363 0.06980 0.06650 -0.0678 0.9426 0.0249
-5.500 -0.1020 0.06337 0.05997 -0.0765 0.9318 0.0140
-5.250 -0.0756 0.05856 0.05510 -0.0818 0.9227 0.0132
-5.000 -0.0416 0.05404 0.05049 -0.0884 0.9140 0.0129
-4.750 -0.0078 0.04964 0.04598 -0.0946 0.9027 0.0128
-4.500 0.0310 0.04500 0.04117 -0.1012 0.8920 0.0139
-4.250 0.0676 0.03998 0.03598 -0.1071 0.8822 0.0146
-4.000 0.1016 0.03510 0.03086 -0.1117 0.8735 0.0148
-3.750 0.1328 0.03115 0.02666 -0.1149 0.8646 0.0154
-3.500 0.1635 0.02841 0.02366 -0.1169 0.8569 0.0168
-3.250 0.1936 0.02572 0.02070 -0.1184 0.8488 0.0203
-3.000 0.2269 0.01801 0.01195 -0.1204 0.8422 0.0230
-2.750 0.2547 0.01577 0.00904 -0.1204 0.8351 0.0275
-2.500 0.2820 0.01501 0.00802 -0.1203 0.8285 0.0325
-2.250 0.3090 0.01418 0.00685 -0.1202 0.8214 0.0383
-2.000 0.3361 0.01361 0.00605 -0.1200 0.8149 0.0409
-1.750 0.3629 0.01325 0.00552 -0.1197 0.8078 0.0445
-1.500 0.3900 0.01266 0.00473 -0.1194 0.8020 0.0448
-1.250 0.4164 0.01220 0.00414 -0.1191 0.7952 0.0449
-1.000 0.4434 0.01185 0.00364 -0.1188 0.7894 0.0454
-0.750 0.4695 0.01159 0.00330 -0.1183 0.7822 0.0463
-0.500 0.4963 0.01137 0.00299 -0.1180 0.7759 0.0481
-0.250 0.5224 0.01118 0.00279 -0.1176 0.7690 0.0543
0.000 0.5489 0.01102 0.00267 -0.1173 0.7628 0.0757
0.250 0.5751 0.01096 0.00270 -0.1169 0.7561 0.1096
0.500 0.6016 0.01097 0.00270 -0.1166 0.7492 0.1317
0.750 0.6277 0.01097 0.00271 -0.1162 0.7420 0.1479
1.000 0.6539 0.01095 0.00272 -0.1159 0.7350 0.1701
1.250 0.6797 0.01089 0.00277 -0.1156 0.7277 0.1949
1.500 0.7055 0.01083 0.00281 -0.1151 0.7196 0.2261
1.750 0.7305 0.01071 0.00289 -0.1146 0.7087 0.3047
2.250 0.7974 0.00966 0.00294 -0.1170 0.6813 1.0000
2.500 0.8224 0.00976 0.00301 -0.1164 0.6689 1.0000
2.750 0.8475 0.00988 0.00310 -0.1157 0.6575 1.0000
3.000 0.8726 0.01000 0.00322 -0.1151 0.6461 1.0000
3.250 0.8976 0.01013 0.00339 -0.1145 0.6339 1.0000
3.500 0.9225 0.01026 0.00356 -0.1138 0.6212 1.0000
3.750 0.9473 0.01041 0.00375 -0.1132 0.6080 1.0000
4.000 0.9720 0.01058 0.00397 -0.1125 0.5953 1.0000
4.250 0.9954 0.01079 0.00419 -0.1115 0.5746 1.0000
4.500 1.0123 0.01130 0.00437 -0.1091 0.5123 1.0000
4.750 1.0273 0.01202 0.00471 -0.1066 0.4245 1.0000
5.000 1.0312 0.01378 0.00551 -0.1027 0.2603 1.0000
5.250 1.0269 0.01682 0.00716 -0.0980 0.0304 1.0000
5.500 1.0456 0.01766 0.00809 -0.0964 0.0201 1.0000
5.750 1.0636 0.01855 0.00918 -0.0946 0.0162 1.0000
6.000 1.0815 0.01938 0.01018 -0.0928 0.0137 1.0000
6.250 1.0966 0.02044 0.01139 -0.0906 0.0124 1.0000
6.500 1.1092 0.02170 0.01277 -0.0881 0.0115 1.0000
6.750 1.1190 0.02325 0.01439 -0.0853 0.0103 1.0000
7.000 1.1286 0.02515 0.01637 -0.0824 0.0091 1.0000
7.250 1.1448 0.02664 0.01797 -0.0805 0.0086 1.0000
7.500 1.1637 0.02846 0.01996 -0.0790 0.0082 1.0000
7.750 1.1863 0.03062 0.02228 -0.0780 0.0080 1.0000
8.000 1.2105 0.03310 0.02498 -0.0772 0.0078 1.0000
8.250 1.2332 0.03592 0.02809 -0.0761 0.0077 1.0000
8.500 1.2513 0.03834 0.03080 -0.0746 0.0072 1.0000
8.750 1.2648 0.04006 0.03269 -0.0729 0.0065 1.0000
9.000 1.2747 0.04238 0.03516 -0.0712 0.0059 1.0000
9.250 1.2807 0.04656 0.03969 -0.0688 0.0057 1.0000
9.500 1.2843 0.04972 0.04320 -0.0659 0.0056 1.0000
9.750 1.2839 0.05310 0.04690 -0.0627 0.0057 1.0000
10.000 1.2794 0.05657 0.05062 -0.0594 0.0057 1.0000
11.000 1.2393 0.06831 0.06335 -0.0475 0.0059 1.0000
11.250 1.2210 0.07300 0.06843 -0.0455 0.0063 1.0000
11.500 1.2002 0.07834 0.07404 -0.0451 0.0065 1.0000
11.750 1.1806 0.08377 0.07969 -0.0457 0.0067 1.0000
12.000 1.1614 0.08955 0.08565 -0.0473 0.0068 1.0000
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Polar data table (+)
Polar graphs
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