GOE 386 AIRFOIL (goe386-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 386 AIRFOIL (goe386-il) Reynolds number: 200,000 Max Cl/Cd: 59.92 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe386-il-200000-n5.txt Download as CSV file: xf-goe386-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 386 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5369 0.04645 0.04084 -0.1248 0.9347 0.0576
-12.500 -0.5540 0.04217 0.03626 -0.1277 0.9207 0.0580
-12.250 -0.5648 0.03930 0.03309 -0.1277 0.9078 0.0585
-12.000 -0.5749 0.03729 0.03080 -0.1254 0.8940 0.0590
-11.750 -0.5775 0.03535 0.02852 -0.1235 0.8824 0.0595
-11.500 -0.5665 0.03406 0.02707 -0.1222 0.8713 0.0599
-11.250 -0.5501 0.03312 0.02608 -0.1212 0.8602 0.0603
-11.000 -0.5330 0.03219 0.02506 -0.1202 0.8485 0.0608
-10.750 -0.5165 0.03129 0.02407 -0.1191 0.8353 0.0613
-10.500 -0.4991 0.03038 0.02303 -0.1181 0.8215 0.0619
-10.250 -0.4815 0.02950 0.02197 -0.1170 0.8055 0.0626
-10.000 -0.4638 0.02862 0.02089 -0.1158 0.7874 0.0634
-9.750 -0.4459 0.02774 0.01974 -0.1147 0.7679 0.0643
-9.500 -0.4278 0.02693 0.01860 -0.1134 0.7479 0.0651
-9.250 -0.4051 0.02623 0.01783 -0.1127 0.7284 0.0657
-9.000 -0.3827 0.02562 0.01710 -0.1120 0.7105 0.0663
-8.750 -0.3602 0.02506 0.01640 -0.1112 0.6949 0.0669
-8.250 -0.3147 0.02401 0.01505 -0.1097 0.6697 0.0687
-7.750 -0.2680 0.02311 0.01374 -0.1083 0.6513 0.0707
-7.500 -0.2434 0.02255 0.01316 -0.1079 0.6434 0.0715
-7.250 -0.2186 0.02209 0.01265 -0.1074 0.6366 0.0723
-7.000 -0.1937 0.02164 0.01217 -0.1069 0.6299 0.0732
-6.750 -0.1686 0.02124 0.01170 -0.1065 0.6238 0.0743
-6.500 -0.1434 0.02091 0.01125 -0.1060 0.6187 0.0754
-6.250 -0.1176 0.02062 0.01082 -0.1056 0.6143 0.0766
-6.000 -0.0922 0.02015 0.01040 -0.1052 0.6099 0.0776
-5.750 -0.0668 0.01975 0.01002 -0.1048 0.6056 0.0787
-5.500 -0.0412 0.01941 0.00967 -0.1044 0.6015 0.0798
-5.250 -0.0154 0.01913 0.00933 -0.1040 0.5979 0.0811
-5.000 0.0109 0.01891 0.00902 -0.1037 0.5946 0.0825
-4.750 0.0368 0.01861 0.00873 -0.1034 0.5912 0.0838
-4.500 0.0621 0.01827 0.00844 -0.1029 0.5873 0.0853
-4.250 0.0878 0.01801 0.00818 -0.1025 0.5828 0.0868
-4.000 0.1138 0.01781 0.00793 -0.1021 0.5784 0.0883
-3.750 0.1404 0.01766 0.00770 -0.1018 0.5743 0.0900
-3.500 0.1664 0.01744 0.00747 -0.1015 0.5706 0.0921
-3.250 0.1925 0.01723 0.00729 -0.1011 0.5667 0.0944
-3.000 0.2190 0.01707 0.00712 -0.1008 0.5625 0.0970
-2.750 0.2453 0.01690 0.00696 -0.1004 0.5582 0.1000
-2.500 0.2719 0.01675 0.00682 -0.1002 0.5542 0.1048
-2.250 0.2987 0.01661 0.00674 -0.1000 0.5507 0.1164
-2.000 0.3250 0.01647 0.00674 -0.0996 0.5467 0.1435
-1.750 0.3514 0.01639 0.00673 -0.0993 0.5421 0.1631
-1.500 0.3781 0.01633 0.00672 -0.0990 0.5377 0.1787
-1.250 0.4052 0.01631 0.00670 -0.0988 0.5340 0.1925
-1.000 0.4326 0.01632 0.00668 -0.0986 0.5308 0.2027
-0.750 0.4600 0.01633 0.00669 -0.0984 0.5278 0.2128
-0.500 0.4866 0.01631 0.00673 -0.0981 0.5242 0.2227
-0.250 0.5130 0.01629 0.00676 -0.0978 0.5201 0.2333
0.000 0.5394 0.01627 0.00678 -0.0975 0.5160 0.2444
0.250 0.5659 0.01626 0.00678 -0.0972 0.5120 0.2572
0.500 0.5927 0.01626 0.00678 -0.0969 0.5083 0.2719
0.750 0.6186 0.01624 0.00686 -0.0966 0.5044 0.2900
1.000 0.6441 0.01621 0.00694 -0.0962 0.5000 0.3128
1.250 0.6696 0.01617 0.00701 -0.0957 0.4955 0.3415
1.500 0.6949 0.01611 0.00705 -0.0953 0.4911 0.3773
1.750 0.7200 0.01604 0.00709 -0.0948 0.4869 0.4245
2.000 0.7431 0.01589 0.00725 -0.0939 0.4813 0.4939
2.250 0.7646 0.01563 0.00738 -0.0927 0.4756 0.6007
2.500 0.7840 0.01537 0.00754 -0.0907 0.4705 0.7357
2.750 0.8091 0.01530 0.00779 -0.0894 0.4651 0.8697
3.000 0.8524 0.01544 0.00801 -0.0923 0.4576 0.9524
3.250 0.8937 0.01563 0.00811 -0.0951 0.4505 0.9897
3.500 0.9231 0.01580 0.00825 -0.0957 0.4429 1.0000
3.750 0.9401 0.01595 0.00834 -0.0937 0.4351 1.0000
4.000 0.9575 0.01612 0.00845 -0.0918 0.4270 1.0000
4.250 0.9743 0.01631 0.00859 -0.0898 0.4176 1.0000
4.500 0.9911 0.01654 0.00875 -0.0879 0.4082 1.0000
4.750 1.0058 0.01679 0.00892 -0.0856 0.3986 1.0000
5.000 1.0204 0.01707 0.00914 -0.0833 0.3893 1.0000
5.250 1.0336 0.01743 0.00940 -0.0809 0.3806 1.0000
5.500 1.0492 0.01780 0.00972 -0.0790 0.3724 1.0000
5.750 1.0635 0.01825 0.01008 -0.0769 0.3649 1.0000
6.000 1.0792 0.01871 0.01048 -0.0752 0.3583 1.0000
6.250 1.0950 0.01921 0.01093 -0.0736 0.3519 1.0000
6.500 1.1094 0.01978 0.01142 -0.0718 0.3463 1.0000
6.750 1.1265 0.02031 0.01192 -0.0705 0.3413 1.0000
7.000 1.1432 0.02086 0.01245 -0.0692 0.3366 1.0000
7.250 1.1595 0.02147 0.01301 -0.0678 0.3325 1.0000
7.500 1.1753 0.02211 0.01359 -0.0665 0.3289 1.0000
7.750 1.1927 0.02271 0.01418 -0.0654 0.3257 1.0000
8.000 1.2105 0.02331 0.01480 -0.0645 0.3225 1.0000
8.250 1.2273 0.02396 0.01545 -0.0634 0.3191 1.0000
8.500 1.2434 0.02466 0.01613 -0.0623 0.3159 1.0000
8.750 1.2594 0.02539 0.01682 -0.0612 0.3128 1.0000
9.000 1.2763 0.02611 0.01748 -0.0602 0.3101 1.0000
9.250 1.2934 0.02680 0.01821 -0.0594 0.3078 1.0000
9.500 1.3098 0.02754 0.01901 -0.0585 0.3053 1.0000
9.750 1.3252 0.02835 0.01985 -0.0575 0.3026 1.0000
10.000 1.3399 0.02920 0.02072 -0.0566 0.2997 1.0000
10.250 1.3540 0.03010 0.02160 -0.0556 0.2966 1.0000
10.500 1.3692 0.03095 0.02241 -0.0547 0.2937 1.0000
10.750 1.3843 0.03183 0.02329 -0.0538 0.2910 1.0000
11.000 1.3959 0.03292 0.02448 -0.0528 0.2884 1.0000
11.250 1.4081 0.03402 0.02565 -0.0519 0.2858 1.0000
11.500 1.4198 0.03516 0.02684 -0.0511 0.2831 1.0000
11.750 1.4316 0.03629 0.02800 -0.0502 0.2805 1.0000
12.000 1.4441 0.03738 0.02909 -0.0494 0.2778 1.0000
12.250 1.4589 0.03833 0.03000 -0.0487 0.2754 1.0000
12.500 1.4683 0.03971 0.03146 -0.0479 0.2729 1.0000
12.750 1.4749 0.04137 0.03324 -0.0471 0.2701 1.0000
13.000 1.4819 0.04302 0.03498 -0.0464 0.2672 1.0000
13.250 1.4903 0.04460 0.03663 -0.0458 0.2646 1.0000
13.500 1.4998 0.04608 0.03814 -0.0452 0.2622 1.0000
13.750 1.5112 0.04739 0.03945 -0.0447 0.2599 1.0000
14.000 1.5243 0.04854 0.04058 -0.0442 0.2577 1.0000
14.250 1.5265 0.05084 0.04304 -0.0437 0.2552 1.0000
14.500 1.5295 0.05310 0.04543 -0.0433 0.2525 1.0000
14.750 1.5333 0.05531 0.04773 -0.0430 0.2499 1.0000
15.000 1.5383 0.05739 0.04989 -0.0427 0.2473 1.0000
15.250 1.5455 0.05924 0.05176 -0.0424 0.2449 1.0000
15.500 1.5564 0.06063 0.05315 -0.0421 0.2426 1.0000
15.750 1.5573 0.06324 0.05587 -0.0420 0.2401 1.0000
16.000 1.5528 0.06654 0.05933 -0.0419 0.2370 1.0000
16.250 1.5501 0.06965 0.06256 -0.0419 0.2338 1.0000
16.500 1.5520 0.07222 0.06520 -0.0419 0.2309 1.0000
16.750 1.5587 0.07418 0.06717 -0.0419 0.2283 1.0000
17.000 1.5609 0.07670 0.06974 -0.0419 0.2256 1.0000
17.250 1.5456 0.08155 0.07480 -0.0424 0.2217 1.0000
17.500 1.5372 0.08557 0.07893 -0.0428 0.2180 1.0000
17.750 1.5393 0.08821 0.08160 -0.0431 0.2148 1.0000
18.000 1.5464 0.09017 0.08355 -0.0432 0.2119 1.0000
18.250 1.5154 0.09736 0.09100 -0.0445 0.2066 1.0000
18.500 1.5072 0.10154 0.09524 -0.0453 0.2022 1.0000
18.750 1.5185 0.10295 0.09660 -0.0455 0.1990 1.0000
19.000 1.4756 0.11219 0.10610 -0.0478 0.1924 1.0000
19.250 1.4745 0.11544 0.10936 -0.0487 0.1881 1.0000
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