GOE 11K AIRFOIL (goe11k-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 11K AIRFOIL (goe11k-il) Reynolds number: 500,000 Max Cl/Cd: 109.45 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe11k-il-500000.txt Download as CSV file: xf-goe11k-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 11K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5180 0.09241 0.09025 -0.0229 0.9994 0.0241
-8.250 -0.5107 0.08777 0.08562 -0.0279 0.9969 0.0250
-7.750 -0.5982 0.02941 0.02571 -0.0639 0.9750 0.0164
-7.500 -0.5691 0.02893 0.02520 -0.0653 0.9739 0.0173
-7.250 -0.5324 0.03082 0.02725 -0.0670 0.9733 0.0181
-7.000 -0.5363 0.02476 0.02045 -0.0628 0.9665 0.0190
-6.750 -0.5173 0.02147 0.01659 -0.0620 0.9642 0.0198
-6.500 -0.4917 0.01964 0.01436 -0.0620 0.9628 0.0208
-6.250 -0.4668 0.01747 0.01178 -0.0619 0.9618 0.0222
-6.000 -0.4352 0.01704 0.01131 -0.0629 0.9610 0.0239
-5.750 -0.4203 0.01680 0.01100 -0.0603 0.9556 0.0253
-5.500 -0.3932 0.01632 0.01038 -0.0602 0.9534 0.0271
-5.250 -0.3661 0.01532 0.00925 -0.0602 0.9519 0.0296
-5.000 -0.3341 0.01526 0.00918 -0.0612 0.9506 0.0322
-4.750 -0.3018 0.01505 0.00889 -0.0622 0.9496 0.0351
-4.500 -0.2706 0.01456 0.00836 -0.0631 0.9487 0.0389
-4.250 -0.2515 0.01457 0.00836 -0.0613 0.9444 0.0420
-4.000 -0.2250 0.01460 0.00833 -0.0610 0.9415 0.0452
-3.750 -0.1973 0.01384 0.00752 -0.0611 0.9398 0.0496
-3.500 -0.1664 0.01360 0.00726 -0.0619 0.9384 0.0535
-3.250 -0.1344 0.01342 0.00704 -0.0628 0.9372 0.0571
-3.000 -0.1036 0.01290 0.00647 -0.0636 0.9363 0.0605
-2.750 -0.0722 0.01246 0.00604 -0.0644 0.9356 0.0644
-2.500 -0.0569 0.01237 0.00594 -0.0618 0.9302 0.0670
-2.250 -0.0296 0.01214 0.00569 -0.0617 0.9277 0.0696
-2.000 0.0005 0.01191 0.00544 -0.0622 0.9260 0.0717
-1.750 0.0320 0.01152 0.00503 -0.0630 0.9247 0.0741
-1.500 0.0661 0.01110 0.00464 -0.0643 0.9236 0.0785
-1.250 0.1018 0.01076 0.00431 -0.0660 0.9228 0.0828
-1.000 0.1382 0.01046 0.00401 -0.0677 0.9221 0.0866
-0.750 0.1519 0.01043 0.00403 -0.0646 0.9155 0.0948
-0.500 0.1816 0.00997 0.00386 -0.0651 0.9134 0.1672
-0.250 0.2042 0.00874 0.00376 -0.0644 0.9116 0.5173
0.000 0.3808 0.00750 0.00392 -0.0978 0.9251 0.9959
0.250 0.4380 0.00727 0.00367 -0.1042 0.9245 1.0000
0.500 0.4829 0.00706 0.00346 -0.1080 0.9228 1.0000
0.750 0.5152 0.00683 0.00323 -0.1087 0.9143 1.0000
1.000 0.5641 0.00651 0.00288 -0.1131 0.9046 1.0000
1.250 0.6002 0.00633 0.00266 -0.1146 0.8864 1.0000
1.500 0.6350 0.00624 0.00252 -0.1158 0.8661 1.0000
1.750 0.6579 0.00623 0.00249 -0.1146 0.8465 1.0000
2.000 0.6806 0.00626 0.00244 -0.1132 0.8182 1.0000
2.250 0.6994 0.00639 0.00237 -0.1108 0.7629 1.0000
2.500 0.7001 0.00696 0.00241 -0.1044 0.6465 1.0000
2.750 0.6797 0.00831 0.00280 -0.0939 0.4504 1.0000
3.000 0.6831 0.00917 0.00313 -0.0888 0.3325 1.0000
3.250 0.6846 0.01036 0.00352 -0.0836 0.1623 1.0000
3.500 0.6979 0.01102 0.00385 -0.0807 0.0990 1.0000
3.750 0.7163 0.01137 0.00412 -0.0787 0.0865 1.0000
4.000 0.7360 0.01164 0.00438 -0.0770 0.0805 1.0000
4.250 0.7538 0.01205 0.00478 -0.0749 0.0737 1.0000
4.500 0.7744 0.01226 0.00502 -0.0734 0.0700 1.0000
4.750 0.7938 0.01257 0.00533 -0.0716 0.0655 1.0000
5.000 0.8108 0.01308 0.00584 -0.0694 0.0600 1.0000
5.250 0.8321 0.01324 0.00606 -0.0681 0.0558 1.0000
5.500 0.8508 0.01364 0.00643 -0.0662 0.0500 1.0000
5.750 0.8701 0.01400 0.00683 -0.0645 0.0450 1.0000
6.000 0.8906 0.01422 0.00703 -0.0630 0.0396 1.0000
6.250 0.9082 0.01472 0.00755 -0.0609 0.0352 1.0000
6.500 0.9278 0.01500 0.00783 -0.0592 0.0314 1.0000
6.750 0.9431 0.01576 0.00860 -0.0568 0.0281 1.0000
7.000 0.9621 0.01612 0.00902 -0.0550 0.0260 1.0000
7.250 0.9805 0.01656 0.00949 -0.0532 0.0241 1.0000
7.500 0.9969 0.01737 0.01032 -0.0510 0.0222 1.0000
7.750 1.0146 0.01857 0.01165 -0.0492 0.0209 1.0000
8.000 1.0343 0.01935 0.01254 -0.0477 0.0201 1.0000
8.250 1.0535 0.02005 0.01332 -0.0461 0.0189 1.0000
8.500 1.0714 0.02063 0.01395 -0.0444 0.0177 1.0000
8.750 1.0894 0.02146 0.01484 -0.0427 0.0170 1.0000
9.000 1.1133 0.02452 0.01818 -0.0428 0.0157 1.0000
9.250 1.1306 0.02556 0.01940 -0.0410 0.0154 1.0000
9.500 1.1466 0.02699 0.02105 -0.0390 0.0150 1.0000
9.750 1.1601 0.02875 0.02307 -0.0366 0.0146 1.0000
10.000 1.1705 0.03046 0.02502 -0.0338 0.0140 1.0000
10.250 1.1787 0.03170 0.02642 -0.0306 0.0135 1.0000
10.500 1.1830 0.03348 0.02842 -0.0269 0.0132 1.0000
10.750 1.1861 0.03491 0.03002 -0.0231 0.0129 1.0000
11.000 1.1938 0.03513 0.03025 -0.0201 0.0124 1.0000
11.250 1.1906 0.03742 0.03278 -0.0158 0.0123 1.0000
11.500 1.1834 0.03984 0.03540 -0.0114 0.0120 1.0000
11.750 1.1703 0.04281 0.03863 -0.0067 0.0119 1.0000
12.000 1.1539 0.04607 0.04218 -0.0022 0.0119 1.0000
12.250 1.1299 0.05006 0.04643 0.0021 0.0118 1.0000
12.500 1.1026 0.05464 0.05128 0.0053 0.0118 1.0000
12.750 1.0890 0.05807 0.05491 0.0070 0.0119 1.0000
13.000 1.0635 0.06328 0.06032 0.0075 0.0118 1.0000
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