GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.37 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe188-il-1000000-n5.txt Download as CSV file: xf-goe188-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2221 0.08007 0.07799 -0.0323 0.7908 0.0034
-7.750 -0.3133 0.08980 0.08771 -0.0262 0.8118 0.0034
-5.750 -0.2039 0.05825 0.05566 -0.0582 0.7134 0.0035
-5.500 -0.1840 0.05482 0.05214 -0.0611 0.7029 0.0036
-5.250 -0.1616 0.05137 0.04858 -0.0641 0.6931 0.0038
-5.000 -0.1374 0.04783 0.04490 -0.0668 0.6825 0.0039
-4.750 -0.1121 0.04439 0.04132 -0.0691 0.6719 0.0040
-4.500 -0.0861 0.04109 0.03787 -0.0709 0.6630 0.0041
-4.250 -0.0594 0.03793 0.03455 -0.0724 0.6554 0.0043
-4.000 -0.0321 0.03492 0.03137 -0.0735 0.6490 0.0045
-3.750 -0.0041 0.03208 0.02835 -0.0743 0.6420 0.0047
-3.500 0.0266 0.02947 0.02552 -0.0744 0.6357 0.0052
-3.250 0.0561 0.02700 0.02283 -0.0744 0.6292 0.0053
-3.000 0.0845 0.02470 0.02030 -0.0745 0.6237 0.0053
-2.750 0.1131 0.02248 0.01787 -0.0745 0.6179 0.0053
-2.500 0.1395 0.01999 0.01514 -0.0750 0.6113 0.0048
-2.250 0.1690 0.01786 0.01274 -0.0748 0.6051 0.0043
-2.000 0.1987 0.01610 0.01071 -0.0745 0.5977 0.0044
-1.750 0.2284 0.01462 0.00900 -0.0742 0.5913 0.0049
-1.500 0.2580 0.01347 0.00764 -0.0739 0.5841 0.0052
-1.250 0.2869 0.01218 0.00615 -0.0738 0.5769 0.0050
-1.000 0.3157 0.01114 0.00494 -0.0737 0.5679 0.0049
-0.750 0.3443 0.01021 0.00387 -0.0735 0.5573 0.0048
-0.500 0.3726 0.00945 0.00298 -0.0734 0.5446 0.0050
-0.250 0.4008 0.00898 0.00238 -0.0734 0.5301 0.0055
0.000 0.4289 0.00879 0.00212 -0.0735 0.5118 0.0063
0.250 0.4569 0.00878 0.00201 -0.0736 0.4895 0.0075
0.750 0.5127 0.00863 0.00155 -0.0738 0.4414 0.0094
1.000 0.5404 0.00870 0.00151 -0.0739 0.4203 0.0119
1.250 0.5683 0.00876 0.00148 -0.0740 0.4040 0.0137
1.500 0.5964 0.00881 0.00142 -0.0741 0.3918 0.0189
1.750 0.6238 0.00773 0.00157 -0.0749 0.3799 0.5898
2.250 0.6740 0.00694 0.00169 -0.0738 0.3611 1.0000
2.500 0.7020 0.00706 0.00174 -0.0739 0.3530 1.0000
2.750 0.7299 0.00719 0.00182 -0.0740 0.3451 1.0000
3.000 0.7577 0.00732 0.00189 -0.0742 0.3371 1.0000
3.250 0.7856 0.00744 0.00198 -0.0743 0.3310 1.0000
3.500 0.8134 0.00756 0.00207 -0.0745 0.3249 1.0000
3.750 0.8411 0.00770 0.00218 -0.0746 0.3190 1.0000
4.000 0.8689 0.00782 0.00228 -0.0747 0.3131 1.0000
4.250 0.8965 0.00797 0.00241 -0.0749 0.3068 1.0000
4.500 0.9240 0.00811 0.00253 -0.0750 0.2988 1.0000
4.750 0.9513 0.00829 0.00268 -0.0751 0.2902 1.0000
5.000 0.9784 0.00846 0.00283 -0.0752 0.2792 1.0000
5.250 1.0055 0.00865 0.00299 -0.0752 0.2680 1.0000
5.500 1.0322 0.00887 0.00317 -0.0753 0.2544 1.0000
5.750 1.0587 0.00912 0.00337 -0.0753 0.2400 1.0000
6.000 1.0845 0.00944 0.00361 -0.0752 0.2206 1.0000
6.250 1.1102 0.00976 0.00387 -0.0751 0.2018 1.0000
6.500 1.1354 0.01014 0.00418 -0.0749 0.1828 1.0000
6.750 1.1587 0.01073 0.00462 -0.0745 0.1533 1.0000
7.000 1.1794 0.01162 0.00521 -0.0738 0.1005 1.0000
7.250 1.1989 0.01263 0.00597 -0.0728 0.0554 1.0000
7.500 1.2220 0.01319 0.00646 -0.0724 0.0405 1.0000
7.750 1.2444 0.01379 0.00699 -0.0718 0.0263 1.0000
8.000 1.2638 0.01472 0.00784 -0.0707 0.0054 1.0000
8.250 1.2865 0.01524 0.00839 -0.0702 0.0036 1.0000
8.500 1.3092 0.01573 0.00894 -0.0696 0.0028 1.0000
8.750 1.3312 0.01626 0.00953 -0.0690 0.0023 1.0000
9.000 1.3519 0.01690 0.01027 -0.0681 0.0020 1.0000
9.250 1.3726 0.01751 0.01095 -0.0673 0.0018 1.0000
9.500 1.3922 0.01817 0.01168 -0.0663 0.0016 1.0000
9.750 1.4112 0.01884 0.01242 -0.0652 0.0014 1.0000
10.000 1.4261 0.01982 0.01350 -0.0636 0.0012 1.0000
10.250 1.4436 0.02051 0.01426 -0.0624 0.0011 1.0000
10.500 1.4581 0.02137 0.01521 -0.0607 0.0010 1.0000
10.750 1.4697 0.02231 0.01626 -0.0586 0.0009 1.0000
11.000 1.4769 0.02330 0.01734 -0.0558 0.0009 1.0000
11.250 1.4834 0.02440 0.01854 -0.0531 0.0008 1.0000
11.500 1.4890 0.02567 0.01992 -0.0507 0.0008 1.0000
11.750 1.4941 0.02710 0.02145 -0.0486 0.0007 1.0000
12.000 1.4985 0.02875 0.02323 -0.0469 0.0007 1.0000
12.250 1.5014 0.03067 0.02527 -0.0455 0.0007 1.0000
12.500 1.5017 0.03303 0.02774 -0.0444 0.0006 1.0000
12.750 1.4986 0.03589 0.03075 -0.0434 0.0006 1.0000
13.000 1.4891 0.03963 0.03464 -0.0427 0.0006 1.0000
13.250 1.4857 0.04285 0.03799 -0.0424 0.0005 1.0000
13.500 1.4818 0.04625 0.04153 -0.0423 0.0005 1.0000
13.750 1.4761 0.04996 0.04537 -0.0425 0.0005 1.0000
14.000 1.4687 0.05402 0.04956 -0.0428 0.0005 1.0000
14.250 1.4603 0.05828 0.05397 -0.0433 0.0005 1.0000
14.500 1.4505 0.06288 0.05870 -0.0441 0.0005 1.0000
14.750 1.4393 0.06790 0.06386 -0.0452 0.0005 1.0000
15.000 1.4279 0.07314 0.06923 -0.0465 0.0005 1.0000
15.250 1.4160 0.07865 0.07487 -0.0481 0.0005 1.0000
15.500 1.4040 0.08434 0.08070 -0.0499 0.0005 1.0000
15.750 1.3914 0.09022 0.08671 -0.0518 0.0005 1.0000
16.000 1.3783 0.09626 0.09288 -0.0539 0.0004 1.0000
16.250 1.3652 0.10244 0.09919 -0.0561 0.0004 1.0000
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Polar data table (+)
Polar graphs
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