GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 479 AIRFOIL (goe479-il) Reynolds number: 50,000 Max Cl/Cd: 35.43 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe479-il-50000-n5.txt Download as CSV file: xf-goe479-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 479 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3385 0.11132 0.10398 -0.0374 1.0000 0.1443
-9.250 -0.3491 0.10922 0.10198 -0.0380 1.0000 0.1449
-8.750 -0.3710 0.09537 0.08819 -0.0426 1.0000 0.0862
-8.500 -0.3703 0.09277 0.08566 -0.0410 1.0000 0.0851
-8.250 -0.3777 0.09025 0.08324 -0.0397 1.0000 0.0841
-8.000 -0.3905 0.08787 0.08097 -0.0381 1.0000 0.0832
-7.750 -0.4042 0.08511 0.07831 -0.0373 1.0000 0.0826
-7.500 -0.4171 0.08203 0.07532 -0.0370 1.0000 0.0823
-7.250 -0.4290 0.07877 0.07212 -0.0369 1.0000 0.0819
-7.000 -0.4395 0.07535 0.06872 -0.0369 1.0000 0.0817
-6.750 -0.4482 0.07179 0.06515 -0.0370 1.0000 0.0817
-6.500 -0.4525 0.06787 0.06115 -0.0377 0.9994 0.0815
-6.250 -0.4304 0.06161 0.05460 -0.0446 0.9903 0.0811
-6.000 -0.4072 0.05576 0.04834 -0.0503 0.9815 0.0808
-5.750 -0.3818 0.05089 0.04301 -0.0548 0.9730 0.0818
-5.500 -0.3573 0.04669 0.03828 -0.0579 0.9640 0.0838
-5.250 -0.3293 0.04292 0.03387 -0.0606 0.9561 0.0853
-5.000 -0.3008 0.03981 0.03015 -0.0625 0.9479 0.0863
-4.750 -0.2720 0.03774 0.02780 -0.0638 0.9401 0.0881
-4.500 -0.2412 0.03642 0.02635 -0.0652 0.9321 0.0913
-4.250 -0.2110 0.03488 0.02448 -0.0663 0.9241 0.0948
-4.000 -0.1791 0.03323 0.02238 -0.0673 0.9162 0.0976
-3.750 -0.1464 0.03187 0.02072 -0.0684 0.9086 0.1010
-3.500 -0.1157 0.03104 0.01985 -0.0693 0.8999 0.1062
-3.250 -0.0818 0.03006 0.01859 -0.0703 0.8921 0.1124
-3.000 -0.0496 0.02920 0.01770 -0.0711 0.8832 0.1184
-2.750 -0.0155 0.02850 0.01682 -0.0720 0.8748 0.1284
-2.500 0.0197 0.02776 0.01609 -0.0732 0.8664 0.1395
-2.250 0.0523 0.02714 0.01545 -0.0740 0.8574 0.1558
-2.000 0.0881 0.02645 0.01477 -0.0752 0.8495 0.1808
-1.750 0.1172 0.02587 0.01434 -0.0754 0.8400 0.2163
-1.500 0.1513 0.02512 0.01386 -0.0765 0.8324 0.2775
-1.250 0.1761 0.02444 0.01364 -0.0761 0.8224 0.3658
-1.000 0.2343 0.02238 0.01354 -0.0798 0.8181 0.8803
-0.750 0.2887 0.02228 0.01305 -0.0847 0.8111 1.0000
-0.500 0.3157 0.02237 0.01287 -0.0843 0.8007 1.0000
-0.250 0.3415 0.02249 0.01276 -0.0838 0.7901 1.0000
0.000 0.3751 0.02245 0.01249 -0.0845 0.7821 1.0000
0.250 0.3976 0.02267 0.01254 -0.0834 0.7706 1.0000
0.500 0.4303 0.02266 0.01234 -0.0839 0.7624 1.0000
1.000 0.4806 0.02303 0.01246 -0.0825 0.7410 1.0000
1.250 0.5125 0.02304 0.01234 -0.0828 0.7323 1.0000
1.500 0.5346 0.02335 0.01256 -0.0817 0.7207 1.0000
1.750 0.5658 0.02340 0.01250 -0.0818 0.7120 1.0000
2.000 0.5898 0.02367 0.01270 -0.0809 0.7007 1.0000
2.250 0.6139 0.02396 0.01294 -0.0801 0.6898 1.0000
2.500 0.6458 0.02399 0.01289 -0.0803 0.6809 1.0000
2.750 0.6660 0.02441 0.01329 -0.0789 0.6685 1.0000
3.000 0.6917 0.02466 0.01350 -0.0782 0.6578 1.0000
3.250 0.7206 0.02477 0.01357 -0.0779 0.6475 1.0000
3.500 0.7409 0.02518 0.01398 -0.0765 0.6346 1.0000
3.750 0.7652 0.02544 0.01422 -0.0756 0.6227 1.0000
4.000 0.7957 0.02545 0.01419 -0.0754 0.6121 1.0000
4.250 0.8143 0.02589 0.01465 -0.0737 0.5984 1.0000
4.500 0.8351 0.02627 0.01507 -0.0723 0.5857 1.0000
4.750 0.8597 0.02652 0.01532 -0.0714 0.5742 1.0000
5.000 0.8850 0.02673 0.01554 -0.0706 0.5626 1.0000
5.250 0.9031 0.02724 0.01613 -0.0689 0.5497 1.0000
5.500 0.9238 0.02765 0.01659 -0.0676 0.5376 1.0000
5.750 0.9483 0.02790 0.01686 -0.0667 0.5262 1.0000
6.000 0.9704 0.02824 0.01726 -0.0655 0.5141 1.0000
6.250 0.9884 0.02877 0.01788 -0.0639 0.5013 1.0000
6.500 1.0087 0.02922 0.01839 -0.0625 0.4890 1.0000
6.750 1.0323 0.02954 0.01874 -0.0615 0.4774 1.0000
7.000 1.0545 0.02993 0.01921 -0.0603 0.4653 1.0000
7.250 1.0714 0.03058 0.01996 -0.0586 0.4524 1.0000
7.500 1.0905 0.03117 0.02063 -0.0572 0.4401 1.0000
7.750 1.1130 0.03162 0.02115 -0.0561 0.4283 1.0000
8.000 1.1339 0.03200 0.02156 -0.0547 0.4146 1.0000
8.250 1.1465 0.03260 0.02221 -0.0523 0.3988 1.0000
8.500 1.1575 0.03313 0.02277 -0.0496 0.3821 1.0000
8.750 1.1655 0.03370 0.02335 -0.0467 0.3649 1.0000
9.000 1.1691 0.03443 0.02414 -0.0432 0.3485 1.0000
9.250 1.1724 0.03525 0.02501 -0.0399 0.3330 1.0000
9.500 1.1746 0.03623 0.02604 -0.0367 0.3175 1.0000
9.750 1.1756 0.03735 0.02718 -0.0338 0.3013 1.0000
10.000 1.1754 0.03867 0.02855 -0.0310 0.2845 1.0000
10.250 1.1756 0.04013 0.03006 -0.0286 0.2679 1.0000
10.500 1.1757 0.04178 0.03175 -0.0265 0.2517 1.0000
10.750 1.1754 0.04363 0.03363 -0.0246 0.2358 1.0000
11.000 1.1737 0.04574 0.03579 -0.0230 0.2193 1.0000
11.250 1.1703 0.04818 0.03826 -0.0217 0.2019 1.0000
11.500 1.1659 0.05089 0.04102 -0.0207 0.1843 1.0000
11.750 1.1600 0.05392 0.04404 -0.0199 0.1666 1.0000
12.000 1.1534 0.05721 0.04728 -0.0194 0.1504 1.0000
12.250 1.1470 0.06065 0.05069 -0.0191 0.1367 1.0000
12.500 1.1411 0.06419 0.05421 -0.0190 0.1253 1.0000
12.750 1.1368 0.06767 0.05767 -0.0189 0.1165 1.0000
13.000 1.1328 0.07113 0.06108 -0.0191 0.1104 1.0000
13.250 1.1321 0.07440 0.06441 -0.0191 0.1046 1.0000
13.500 1.1318 0.07758 0.06762 -0.0192 0.1003 1.0000
13.750 1.1335 0.08051 0.07051 -0.0191 0.0970 1.0000
14.000 1.1361 0.08359 0.07378 -0.0192 0.0937 1.0000
14.500 1.1416 0.08957 0.07993 -0.0196 0.0879 1.0000
14.750 1.1460 0.09235 0.08273 -0.0197 0.0855 1.0000
15.000 1.1445 0.09641 0.08705 -0.0206 0.0834 1.0000
15.250 1.1427 0.10058 0.09144 -0.0217 0.0815 1.0000
15.500 1.1404 0.10491 0.09597 -0.0229 0.0801 1.0000
15.750 1.1369 0.10950 0.10073 -0.0244 0.0788 1.0000
16.000 1.1343 0.11396 0.10533 -0.0259 0.0775 1.0000
16.250 1.1443 0.11587 0.10724 -0.0257 0.0757 1.0000
16.500 1.1245 0.12403 0.11565 -0.0299 0.0751 1.0000
16.750 1.0920 0.13560 0.12748 -0.0366 0.0750 1.0000
17.000 1.0449 0.15238 0.14447 -0.0466 0.0752 1.0000
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