GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Reynolds number: 50,000 Max Cl/Cd: 31.65 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe188-il-50000.txt Download as CSV file: xf-goe188-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4159 0.10264 0.09642 -0.0153 1.0000 0.1639
-7.500 -0.4009 0.09795 0.09176 -0.0135 1.0000 0.1743
-7.250 -0.4147 0.09677 0.09072 -0.0204 1.0000 0.1790
-7.000 -0.4031 0.09251 0.08653 -0.0183 1.0000 0.1924
-6.750 -0.3952 0.08883 0.08292 -0.0175 1.0000 0.2057
-6.500 -0.3908 0.08564 0.07981 -0.0181 1.0000 0.2201
-6.250 -0.3908 0.08303 0.07727 -0.0204 1.0000 0.2362
-6.000 -0.3793 0.07905 0.07340 -0.0161 1.0000 0.2565
-5.750 -0.3829 0.07700 0.07143 -0.0183 1.0000 0.2801
-5.500 -0.3785 0.07403 0.06859 -0.0150 1.0000 0.3092
-5.250 -0.3691 0.07086 0.06555 -0.0083 1.0000 0.3449
-5.000 -0.0153 0.04767 0.04137 -0.0159 1.0000 1.0000
-4.750 -0.0027 0.04536 0.03913 -0.0173 1.0000 1.0000
-4.500 0.0098 0.04312 0.03695 -0.0188 1.0000 1.0000
-4.250 0.0223 0.04095 0.03486 -0.0202 1.0000 1.0000
-4.000 -0.0301 0.04312 0.03726 -0.0067 1.0000 0.9616
-3.750 -0.0838 0.04483 0.03922 0.0050 1.0000 0.9134
-3.500 -0.1313 0.04536 0.04004 0.0132 1.0000 0.8588
-3.250 -0.1771 0.04569 0.04068 0.0212 1.0000 0.8283
-3.000 -0.2209 0.04591 0.04115 0.0296 1.0000 0.8141
-2.750 -0.2630 0.04594 0.04137 0.0378 1.0000 0.8043
-2.500 -0.3063 0.04576 0.04137 0.0465 1.0000 0.8019
-2.250 -0.2660 0.04026 0.03503 -0.0091 1.0000 0.4978
-2.000 -0.1381 0.03629 0.02840 -0.0370 1.0000 0.2185
-1.750 -0.1027 0.03486 0.02624 -0.0378 1.0000 0.1757
-1.500 -0.0719 0.03399 0.02467 -0.0377 1.0000 0.1497
-1.250 -0.0448 0.03294 0.02322 -0.0375 1.0000 0.1351
-1.000 -0.0191 0.03172 0.02179 -0.0375 1.0000 0.1259
-0.750 0.0300 0.03084 0.02045 -0.0410 0.9917 0.1192
-0.500 0.0862 0.02981 0.01910 -0.0457 0.9790 0.1194
-0.250 0.1419 0.02897 0.01802 -0.0501 0.9658 0.1187
0.000 0.1952 0.02834 0.01718 -0.0545 0.9514 0.1225
0.250 0.2480 0.02766 0.01647 -0.0593 0.9360 0.1454
0.500 0.2954 0.02483 0.01612 -0.0621 0.9218 1.0000
0.750 0.3489 0.02520 0.01571 -0.0660 0.9047 1.0000
1.000 0.4053 0.02540 0.01540 -0.0710 0.8879 1.0000
1.250 0.4438 0.02576 0.01551 -0.0728 0.8676 1.0000
1.500 0.4867 0.02598 0.01553 -0.0751 0.8488 1.0000
1.750 0.5297 0.02608 0.01548 -0.0770 0.8312 1.0000
2.000 0.5572 0.02662 0.01591 -0.0767 0.8099 1.0000
2.250 0.5898 0.02692 0.01613 -0.0767 0.7912 1.0000
2.500 0.6220 0.02716 0.01631 -0.0764 0.7740 1.0000
2.750 0.6426 0.02797 0.01709 -0.0752 0.7531 1.0000
3.000 0.6688 0.02846 0.01754 -0.0744 0.7356 1.0000
3.250 0.6951 0.02894 0.01799 -0.0735 0.7195 1.0000
3.500 0.7208 0.02944 0.01847 -0.0726 0.7040 1.0000
3.750 0.7460 0.02997 0.01904 -0.0716 0.6891 1.0000
4.000 0.7687 0.03073 0.01983 -0.0707 0.6738 1.0000
4.250 0.7910 0.03153 0.02067 -0.0698 0.6588 1.0000
4.500 0.8141 0.03226 0.02145 -0.0689 0.6444 1.0000
4.750 0.8370 0.03296 0.02227 -0.0678 0.6300 1.0000
5.000 0.8601 0.03363 0.02301 -0.0668 0.6157 1.0000
5.250 0.8835 0.03426 0.02372 -0.0657 0.6019 1.0000
5.500 0.9078 0.03482 0.02437 -0.0647 0.5886 1.0000
5.750 0.9321 0.03540 0.02505 -0.0637 0.5757 1.0000
6.000 0.9527 0.03648 0.02634 -0.0628 0.5622 1.0000
6.250 0.9726 0.03763 0.02766 -0.0619 0.5489 1.0000
6.750 1.0104 0.04026 0.03066 -0.0601 0.5225 1.0000
7.000 1.0280 0.04178 0.03238 -0.0592 0.5095 1.0000
7.250 1.0445 0.04348 0.03434 -0.0583 0.4967 1.0000
7.500 1.0611 0.04513 0.03621 -0.0573 0.4838 1.0000
7.750 1.0761 0.04701 0.03831 -0.0562 0.4710 1.0000
8.000 1.0921 0.04869 0.04022 -0.0550 0.4577 1.0000
8.250 1.1470 0.04400 0.03566 -0.0517 0.4336 1.0000
8.500 1.1837 0.04144 0.03312 -0.0490 0.4062 1.0000
8.750 1.2048 0.04143 0.03330 -0.0469 0.3821 1.0000
9.000 1.2268 0.04120 0.03326 -0.0446 0.3552 1.0000
9.250 1.2514 0.04033 0.03238 -0.0420 0.3209 1.0000
9.500 1.2649 0.03997 0.03197 -0.0385 0.2784 1.0000
9.750 1.2750 0.04069 0.03253 -0.0350 0.2377 1.0000
10.000 1.2808 0.04211 0.03390 -0.0318 0.2060 1.0000
10.250 1.2865 0.04375 0.03539 -0.0289 0.1790 1.0000
10.500 1.2872 0.04567 0.03716 -0.0260 0.1548 1.0000
10.750 1.2914 0.04808 0.03926 -0.0236 0.1326 1.0000
11.000 1.2890 0.05102 0.04242 -0.0208 0.1181 1.0000
11.250 1.2941 0.05451 0.04599 -0.0187 0.1059 1.0000
11.500 1.3026 0.05807 0.04952 -0.0172 0.0952 1.0000
11.750 1.2878 0.06158 0.05353 -0.0141 0.0927 1.0000
12.000 1.2755 0.06548 0.05778 -0.0120 0.0900 1.0000
12.250 1.2690 0.06964 0.06218 -0.0108 0.0871 1.0000
12.500 1.0263 0.11724 0.11064 -0.0433 0.1808 1.0000
12.750 1.0015 0.12781 0.12103 -0.0484 0.1826 1.0000
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Polar data table (+)
Polar graphs
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