GOE 370 AIRFOIL (goe370-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 370 AIRFOIL (goe370-il) Reynolds number: 200,000 Max Cl/Cd: 92.01 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe370-il-200000.txt Download as CSV file: xf-goe370-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3180 0.09177 0.08862 -0.0228 1.0000 0.0258
-6.750 -0.3306 0.09088 0.08783 -0.0197 1.0000 0.0262
-6.500 -0.3474 0.09053 0.08757 -0.0159 1.0000 0.0263
-6.250 -0.3178 0.08652 0.08354 -0.0246 0.9949 0.0284
-6.000 -0.2608 0.08338 0.08030 -0.0434 0.9861 0.0299
-5.750 -0.2201 0.07883 0.07567 -0.0532 0.9806 0.0301
-5.500 -0.2048 0.07141 0.06828 -0.0563 0.9746 0.0311
-5.250 -0.1810 0.06690 0.06375 -0.0585 0.9709 0.0325
-5.000 -0.1520 0.06310 0.05988 -0.0633 0.9640 0.0341
-4.750 -0.1147 0.05898 0.05569 -0.0703 0.9590 0.0364
-4.500 0.0067 0.03348 0.03009 -0.0915 0.9429 0.0433
-4.250 0.0157 0.03009 0.02676 -0.0895 0.9352 0.0459
-4.000 0.0733 0.02749 0.02379 -0.1000 0.9312 0.0554
-3.750 0.0871 0.02267 0.01903 -0.1003 0.9255 0.0576
-3.500 0.1121 0.02023 0.01651 -0.1016 0.9193 0.0624
-3.250 0.1534 0.01666 0.01264 -0.1072 0.9156 0.0706
-3.000 0.1642 0.03292 0.02856 -0.1106 0.9245 0.0721
-2.750 0.2012 0.03028 0.02566 -0.1136 0.9189 0.0845
-2.500 0.2412 0.02789 0.02290 -0.1166 0.9151 0.0968
-2.250 0.2726 0.02223 0.01658 -0.1170 0.9069 0.0701
-2.000 0.3063 0.01941 0.01338 -0.1180 0.9023 0.0658
-1.750 0.3338 0.01701 0.01049 -0.1177 0.8945 0.0638
-1.500 0.3655 0.01534 0.00835 -0.1180 0.8892 0.0645
-1.250 0.3929 0.01476 0.00749 -0.1176 0.8815 0.0681
-1.000 0.4228 0.01368 0.00619 -0.1176 0.8753 0.0694
-0.750 0.4488 0.01297 0.00545 -0.1171 0.8672 0.0725
-0.500 0.4778 0.01250 0.00493 -0.1170 0.8608 0.0788
-0.250 0.5028 0.01214 0.00459 -0.1162 0.8522 0.0884
0.000 0.5311 0.01191 0.00440 -0.1160 0.8456 0.1198
0.250 0.5562 0.01182 0.00437 -0.1153 0.8364 0.1655
0.500 0.5823 0.01169 0.00427 -0.1149 0.8284 0.1915
0.750 0.6087 0.01156 0.00421 -0.1144 0.8204 0.2168
1.000 0.6336 0.01146 0.00422 -0.1138 0.8111 0.2432
1.250 0.6591 0.01125 0.00423 -0.1132 0.8024 0.3171
1.500 0.7080 0.00992 0.00402 -0.1175 0.7920 1.0000
1.750 0.7325 0.00998 0.00397 -0.1164 0.7790 1.0000
2.000 0.7570 0.01006 0.00399 -0.1154 0.7665 1.0000
2.250 0.7818 0.01016 0.00404 -0.1146 0.7551 1.0000
2.500 0.8070 0.01028 0.00411 -0.1138 0.7445 1.0000
2.750 0.8327 0.01039 0.00418 -0.1132 0.7345 1.0000
3.000 0.8575 0.01051 0.00430 -0.1124 0.7233 1.0000
3.250 0.8822 0.01064 0.00450 -0.1116 0.7118 1.0000
3.500 0.9071 0.01077 0.00466 -0.1109 0.7007 1.0000
3.750 0.9321 0.01090 0.00483 -0.1101 0.6895 1.0000
4.000 0.9553 0.01090 0.00484 -0.1088 0.6703 1.0000
4.250 0.9763 0.01079 0.00470 -0.1068 0.6382 1.0000
4.500 0.9965 0.01083 0.00465 -0.1047 0.5976 1.0000
4.750 1.0145 0.01114 0.00474 -0.1023 0.5418 1.0000
5.000 1.0200 0.01233 0.00508 -0.0977 0.3751 1.0000
5.250 1.0071 0.01598 0.00675 -0.0916 0.0638 1.0000
5.500 1.0230 0.01720 0.00790 -0.0894 0.0408 1.0000
5.750 1.0405 0.01817 0.00904 -0.0874 0.0359 1.0000
6.000 1.0529 0.01956 0.01056 -0.0847 0.0332 1.0000
6.250 1.0634 0.02122 0.01233 -0.0817 0.0318 1.0000
6.500 1.0814 0.02215 0.01334 -0.0799 0.0291 1.0000
6.750 1.0976 0.02362 0.01487 -0.0778 0.0279 1.0000
7.000 1.1176 0.02539 0.01669 -0.0762 0.0273 1.0000
7.250 1.1433 0.02754 0.01894 -0.0754 0.0275 1.0000
7.500 1.1740 0.03044 0.02199 -0.0752 0.0291 1.0000
7.750 1.2114 0.03592 0.02762 -0.0762 0.0325 1.0000
8.000 1.2337 0.03731 0.02925 -0.0745 0.0332 1.0000
13.500 1.0382 0.14993 0.14668 -0.0744 0.0421 1.0000
13.750 1.0324 0.15803 0.15476 -0.0797 0.0409 1.0000
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Polar data table (+)
Polar graphs
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