GOE 370 AIRFOIL (goe370-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 370 AIRFOIL (goe370-il) Reynolds number: 50,000 Max Cl/Cd: 44.78 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe370-il-50000-n5.txt Download as CSV file: xf-goe370-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3072 0.11259 0.10594 -0.0318 1.0000 0.0599
-8.000 -0.3124 0.11198 0.10546 -0.0317 1.0000 0.0603
-7.750 -0.3177 0.11122 0.10484 -0.0315 1.0000 0.0605
-7.500 -0.3199 0.11030 0.10405 -0.0325 1.0000 0.0607
-7.250 -0.3156 0.10549 0.09933 -0.0308 1.0000 0.0614
-7.000 -0.3086 0.10031 0.09417 -0.0277 1.0000 0.0634
-6.750 -0.3091 0.09798 0.09193 -0.0264 1.0000 0.0650
-6.500 -0.3114 0.09610 0.09015 -0.0253 1.0000 0.0665
-6.250 -0.3147 0.09439 0.08853 -0.0242 1.0000 0.0684
-6.000 -0.3180 0.09285 0.08709 -0.0235 1.0000 0.0702
-5.750 -0.3198 0.09156 0.08586 -0.0238 1.0000 0.0722
-5.500 -0.3175 0.09070 0.08504 -0.0262 1.0000 0.0737
-5.250 -0.3086 0.08972 0.08406 -0.0305 1.0000 0.0744
-5.000 -0.2975 0.08546 0.07984 -0.0315 0.9976 0.0752
-4.750 -0.2839 0.08042 0.07477 -0.0304 0.9924 0.0794
-4.500 -0.2283 0.07804 0.07213 -0.0463 0.9834 0.0884
-4.250 -0.2161 0.07237 0.06654 -0.0447 0.9781 0.0921
-4.000 -0.1834 0.06857 0.06263 -0.0503 0.9701 0.0979
-3.250 -0.0397 0.05412 0.04726 -0.0763 0.9490 0.0606
-2.750 0.0346 0.04604 0.03866 -0.0850 0.9367 0.0598
-2.500 0.0779 0.04203 0.03420 -0.0900 0.9310 0.0602
-2.250 0.1100 0.03985 0.03187 -0.0924 0.9250 0.0701
-2.000 0.1500 0.03654 0.02803 -0.0957 0.9188 0.0708
-1.750 0.1950 0.03340 0.02420 -0.0996 0.9147 0.0759
-1.500 0.2242 0.03214 0.02258 -0.1005 0.9069 0.0851
-1.250 0.2648 0.02992 0.01971 -0.1029 0.9021 0.0860
-1.000 0.2995 0.02831 0.01750 -0.1042 0.8957 0.0876
-0.750 0.3345 0.02712 0.01593 -0.1055 0.8896 0.0910
-0.500 0.3762 0.02618 0.01449 -0.1079 0.8851 0.0981
-0.250 0.4085 0.02559 0.01363 -0.1087 0.8775 0.1090
0.000 0.4480 0.02512 0.01297 -0.1107 0.8727 0.1414
0.250 0.4753 0.02475 0.01258 -0.1108 0.8639 0.1774
0.500 0.5122 0.02426 0.01222 -0.1126 0.8588 0.2356
0.750 0.5377 0.02410 0.01211 -0.1123 0.8494 0.2721
1.000 0.5690 0.02374 0.01195 -0.1130 0.8425 0.3329
1.250 0.6036 0.02250 0.01175 -0.1145 0.8350 1.0000
1.500 0.6322 0.02278 0.01176 -0.1145 0.8266 1.0000
1.750 0.6635 0.02298 0.01178 -0.1150 0.8192 1.0000
2.000 0.6882 0.02335 0.01207 -0.1145 0.8094 1.0000
2.250 0.7212 0.02348 0.01213 -0.1152 0.8028 1.0000
2.500 0.7448 0.02389 0.01252 -0.1145 0.7924 1.0000
2.750 0.7701 0.02424 0.01292 -0.1140 0.7826 1.0000
3.000 0.8031 0.02430 0.01302 -0.1145 0.7752 1.0000
3.250 0.8268 0.02461 0.01339 -0.1136 0.7631 1.0000
3.500 0.8519 0.02483 0.01370 -0.1128 0.7509 1.0000
3.750 0.8776 0.02501 0.01406 -0.1119 0.7386 1.0000
4.000 0.9036 0.02519 0.01438 -0.1111 0.7267 1.0000
4.250 0.9307 0.02532 0.01470 -0.1105 0.7154 1.0000
4.500 0.9587 0.02541 0.01500 -0.1099 0.7044 1.0000
4.750 0.9816 0.02573 0.01563 -0.1087 0.6912 1.0000
5.000 1.0046 0.02604 0.01622 -0.1075 0.6778 1.0000
5.250 1.0279 0.02634 0.01686 -0.1063 0.6642 1.0000
5.500 1.0518 0.02656 0.01747 -0.1049 0.6498 1.0000
5.750 1.0686 0.02432 0.01524 -0.0982 0.5760 1.0000
6.000 1.0760 0.02403 0.01442 -0.0919 0.4550 1.0000
6.250 1.0692 0.02617 0.01508 -0.0858 0.2495 1.0000
6.500 1.0553 0.03023 0.01751 -0.0813 0.0698 1.0000
6.750 1.0616 0.03242 0.01961 -0.0784 0.0521 1.0000
7.000 1.0684 0.03438 0.02173 -0.0756 0.0462 1.0000
7.250 1.0735 0.03633 0.02388 -0.0726 0.0424 1.0000
7.500 1.0790 0.03825 0.02599 -0.0699 0.0382 1.0000
7.750 1.0812 0.04060 0.02843 -0.0671 0.0353 1.0000
8.000 1.0916 0.04249 0.03056 -0.0647 0.0339 1.0000
8.250 1.1129 0.04439 0.03272 -0.0629 0.0323 1.0000
8.500 1.1512 0.04665 0.03529 -0.0627 0.0292 1.0000
8.750 1.2050 0.05119 0.03991 -0.0654 0.0262 1.0000
9.000 1.2322 0.05474 0.04389 -0.0647 0.0259 1.0000
9.250 1.2500 0.05842 0.04803 -0.0633 0.0258 1.0000
9.500 1.2614 0.06222 0.05225 -0.0615 0.0258 1.0000
9.750 1.2671 0.06604 0.05648 -0.0593 0.0258 1.0000
10.000 1.2672 0.06965 0.06048 -0.0568 0.0258 1.0000
10.250 1.2622 0.07316 0.06435 -0.0541 0.0258 1.0000
10.500 1.2527 0.07651 0.06801 -0.0512 0.0258 1.0000
10.750 1.2399 0.07995 0.07174 -0.0486 0.0257 1.0000
11.000 1.2257 0.08362 0.07568 -0.0467 0.0257 1.0000
11.250 1.2117 0.08764 0.07993 -0.0456 0.0258 1.0000
11.500 1.1957 0.09198 0.08449 -0.0453 0.0258 1.0000
11.750 1.1804 0.09671 0.08942 -0.0456 0.0260 1.0000
12.000 1.1650 0.10181 0.09468 -0.0467 0.0261 1.0000
12.250 1.1507 0.10721 0.10023 -0.0483 0.0262 1.0000
12.500 1.1381 0.11294 0.10608 -0.0503 0.0264 1.0000
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Polar data table (+)
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