GOE 617 AIRFOIL (goe617-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 617 AIRFOIL (goe617-il) Reynolds number: 200,000 Max Cl/Cd: 63.03 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe617-il-200000-n5.txt Download as CSV file: xf-goe617-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 617 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.8202 0.05842 0.05365 -0.0747 1.0000 0.0287
-14.000 -0.8472 0.05222 0.04721 -0.0779 1.0000 0.0287
-13.750 -0.8531 0.04941 0.04434 -0.0784 1.0000 0.0291
-13.500 -0.8631 0.04651 0.04132 -0.0782 1.0000 0.0293
-13.250 -0.8701 0.04427 0.03898 -0.0772 1.0000 0.0297
-13.000 -0.8759 0.04240 0.03700 -0.0755 1.0000 0.0302
-12.750 -0.8857 0.04032 0.03476 -0.0729 1.0000 0.0306
-12.500 -0.8942 0.03858 0.03286 -0.0696 1.0000 0.0312
-12.250 -0.9027 0.03704 0.03115 -0.0656 1.0000 0.0318
-12.000 -0.9124 0.03562 0.02953 -0.0609 1.0000 0.0323
-11.750 -0.9232 0.03434 0.02804 -0.0555 1.0000 0.0329
-11.500 -0.9295 0.03314 0.02663 -0.0505 1.0000 0.0334
-11.250 -0.9286 0.03233 0.02582 -0.0466 1.0000 0.0339
-11.000 -0.9266 0.03177 0.02525 -0.0426 1.0000 0.0345
-10.750 -0.9250 0.03120 0.02464 -0.0386 1.0000 0.0351
-10.500 -0.9146 0.03040 0.02375 -0.0363 0.9988 0.0359
-10.250 -0.8882 0.02928 0.02244 -0.0371 0.9948 0.0372
-10.000 -0.8636 0.02799 0.02088 -0.0375 0.9905 0.0386
-9.750 -0.8370 0.02684 0.01957 -0.0382 0.9862 0.0398
-9.500 -0.8077 0.02614 0.01884 -0.0393 0.9825 0.0410
-9.250 -0.7809 0.02538 0.01801 -0.0397 0.9768 0.0422
-9.000 -0.7500 0.02449 0.01698 -0.0409 0.9728 0.0437
-8.750 -0.7226 0.02361 0.01592 -0.0412 0.9671 0.0453
-8.500 -0.6935 0.02276 0.01498 -0.0420 0.9622 0.0468
-8.250 -0.6611 0.02210 0.01429 -0.0433 0.9589 0.0482
-8.000 -0.6355 0.02149 0.01363 -0.0431 0.9523 0.0497
-7.750 -0.6050 0.02084 0.01289 -0.0440 0.9479 0.0519
-7.500 -0.5713 0.02012 0.01205 -0.0454 0.9448 0.0541
-7.250 -0.5446 0.01957 0.01150 -0.0454 0.9386 0.0559
-7.000 -0.5142 0.01902 0.01093 -0.0462 0.9334 0.0582
-6.750 -0.4808 0.01845 0.01026 -0.0474 0.9296 0.0612
-6.500 -0.4528 0.01791 0.00968 -0.0476 0.9235 0.0641
-6.250 -0.4242 0.01744 0.00921 -0.0480 0.9172 0.0673
-6.000 -0.3906 0.01695 0.00865 -0.0492 0.9128 0.0714
-5.750 -0.3649 0.01649 0.00815 -0.0489 0.9053 0.0747
-5.500 -0.3366 0.01598 0.00765 -0.0491 0.8987 0.0786
-5.250 -0.3062 0.01559 0.00719 -0.0497 0.8928 0.0832
-5.000 -0.2819 0.01523 0.00681 -0.0490 0.8841 0.0873
-4.750 -0.2518 0.01478 0.00636 -0.0495 0.8780 0.0926
-4.500 -0.2295 0.01452 0.00606 -0.0483 0.8682 0.0975
-4.250 -0.2009 0.01414 0.00569 -0.0485 0.8612 0.1046
-4.000 -0.1790 0.01388 0.00545 -0.0472 0.8509 0.1132
-3.750 -0.1531 0.01354 0.00517 -0.0468 0.8427 0.1282
-3.500 -0.1305 0.01324 0.00498 -0.0457 0.8325 0.1533
-3.250 -0.1065 0.01296 0.00478 -0.0449 0.8230 0.1856
-3.000 -0.0824 0.01268 0.00454 -0.0441 0.8131 0.2134
-2.750 -0.0604 0.01239 0.00434 -0.0429 0.8020 0.2419
-2.500 -0.0395 0.01196 0.00414 -0.0415 0.7913 0.2978
-2.250 -0.0210 0.01151 0.00400 -0.0396 0.7796 0.3910
-2.000 -0.0021 0.01119 0.00388 -0.0377 0.7668 0.4543
-1.750 0.0163 0.01085 0.00376 -0.0355 0.7538 0.5210
-1.500 0.0355 0.01054 0.00367 -0.0335 0.7405 0.5887
-1.250 0.0564 0.01022 0.00364 -0.0316 0.7272 0.6707
-1.000 0.0875 0.01006 0.00372 -0.0318 0.7134 0.7482
-0.750 0.1299 0.01011 0.00386 -0.0343 0.6997 0.8031
-0.500 0.1714 0.01027 0.00399 -0.0367 0.6862 0.8424
-0.250 0.2114 0.01047 0.00413 -0.0388 0.6728 0.8673
0.000 0.2459 0.01065 0.00422 -0.0398 0.6603 0.8833
0.250 0.2791 0.01084 0.00431 -0.0406 0.6478 0.8974
0.500 0.3070 0.01102 0.00442 -0.0403 0.6355 0.9106
0.750 0.3492 0.01128 0.00459 -0.0430 0.6233 0.9177
1.000 0.3760 0.01147 0.00469 -0.0425 0.6124 0.9277
1.250 0.4141 0.01167 0.00481 -0.0445 0.5983 0.9322
1.500 0.4445 0.01185 0.00492 -0.0449 0.5849 0.9399
1.750 0.4782 0.01203 0.00502 -0.0461 0.5717 0.9458
2.000 0.5132 0.01220 0.00513 -0.0475 0.5594 0.9511
2.250 0.5429 0.01239 0.00525 -0.0479 0.5478 0.9587
2.500 0.5837 0.01256 0.00539 -0.0506 0.5350 0.9641
2.750 0.6147 0.01274 0.00552 -0.0513 0.5226 0.9713
3.000 0.6505 0.01285 0.00559 -0.0531 0.5093 0.9748
3.250 0.6821 0.01298 0.00567 -0.0540 0.4972 0.9789
3.500 0.7113 0.01311 0.00579 -0.0544 0.4851 0.9833
3.750 0.7445 0.01320 0.00585 -0.0558 0.4715 0.9863
4.000 0.7755 0.01332 0.00594 -0.0567 0.4564 0.9898
4.250 0.8042 0.01350 0.00605 -0.0571 0.4367 0.9935
4.500 0.8344 0.01365 0.00612 -0.0579 0.4159 0.9965
4.750 0.8646 0.01383 0.00624 -0.0587 0.3966 0.9995
5.000 0.8835 0.01404 0.00641 -0.0572 0.3802 1.0000
5.250 0.8995 0.01427 0.00659 -0.0550 0.3649 1.0000
5.500 0.9148 0.01453 0.00680 -0.0527 0.3489 1.0000
5.750 0.9296 0.01480 0.00703 -0.0504 0.3325 1.0000
6.000 0.9437 0.01509 0.00728 -0.0479 0.3148 1.0000
6.250 0.9568 0.01542 0.00755 -0.0452 0.2948 1.0000
6.500 0.9687 0.01578 0.00785 -0.0423 0.2734 1.0000
6.750 0.9791 0.01619 0.00818 -0.0392 0.2489 1.0000
7.000 0.9867 0.01670 0.00855 -0.0357 0.2214 1.0000
7.250 0.9931 0.01725 0.00897 -0.0319 0.1989 1.0000
7.500 0.9992 0.01779 0.00941 -0.0281 0.1838 1.0000
7.750 1.0062 0.01827 0.00986 -0.0245 0.1736 1.0000
8.250 1.0153 0.01915 0.01073 -0.0162 0.1591 1.0000
8.500 1.0193 0.01964 0.01120 -0.0121 0.1528 1.0000
8.750 1.0255 0.02013 0.01171 -0.0085 0.1472 1.0000
9.000 1.0338 0.02061 0.01223 -0.0053 0.1411 1.0000
9.250 1.0394 0.02125 0.01286 -0.0019 0.1354 1.0000
9.500 1.0495 0.02178 0.01345 0.0007 0.1299 1.0000
9.750 1.0581 0.02242 0.01411 0.0035 0.1242 1.0000
10.000 1.0653 0.02316 0.01485 0.0062 0.1194 1.0000
10.250 1.0756 0.02383 0.01559 0.0085 0.1148 1.0000
10.500 1.0843 0.02461 0.01640 0.0108 0.1107 1.0000
10.750 1.0912 0.02554 0.01734 0.0131 0.1075 1.0000
11.000 1.1007 0.02640 0.01826 0.0151 0.1043 1.0000
11.250 1.1099 0.02731 0.01924 0.0170 0.1015 1.0000
11.500 1.1182 0.02832 0.02029 0.0188 0.0986 1.0000
11.750 1.1246 0.02948 0.02146 0.0206 0.0956 1.0000
12.000 1.1325 0.03061 0.02265 0.0222 0.0927 1.0000
12.250 1.1416 0.03171 0.02384 0.0236 0.0899 1.0000
12.500 1.1492 0.03295 0.02513 0.0250 0.0868 1.0000
12.750 1.1552 0.03435 0.02657 0.0263 0.0847 1.0000
13.000 1.1592 0.03597 0.02819 0.0276 0.0823 1.0000
13.250 1.1682 0.03725 0.02960 0.0285 0.0801 1.0000
13.500 1.1760 0.03867 0.03114 0.0294 0.0778 1.0000
13.750 1.1819 0.04027 0.03282 0.0302 0.0754 1.0000
14.000 1.1860 0.04210 0.03469 0.0309 0.0733 1.0000
14.250 1.1878 0.04417 0.03678 0.0316 0.0713 1.0000
14.500 1.1955 0.04579 0.03856 0.0320 0.0690 1.0000
14.750 1.2012 0.04765 0.04055 0.0323 0.0665 1.0000
15.000 1.2051 0.04975 0.04275 0.0325 0.0643 1.0000
15.250 1.2065 0.05216 0.04521 0.0325 0.0622 1.0000
15.500 1.2084 0.05457 0.04771 0.0325 0.0603 1.0000
15.750 1.2128 0.05677 0.05005 0.0325 0.0583 1.0000
16.000 1.2153 0.05929 0.05270 0.0322 0.0556 1.0000
16.250 1.2145 0.06224 0.05573 0.0317 0.0533 1.0000
16.500 1.2135 0.06528 0.05885 0.0311 0.0511 1.0000
16.750 1.2145 0.06811 0.06184 0.0305 0.0485 1.0000
17.000 1.2121 0.07150 0.06533 0.0296 0.0458 1.0000
17.250 1.2080 0.07520 0.06913 0.0286 0.0427 1.0000
17.500 1.2037 0.07897 0.07300 0.0274 0.0395 1.0000
17.750 1.1964 0.08325 0.07738 0.0260 0.0367 1.0000
18.000 1.1890 0.08765 0.08189 0.0244 0.0339 1.0000
18.250 1.1773 0.09285 0.08716 0.0224 0.0312 1.0000
18.500 1.1658 0.09806 0.09248 0.0203 0.0293 1.0000
18.750 1.1523 0.10375 0.09827 0.0179 0.0281 1.0000
19.000 1.1367 0.10994 0.10457 0.0152 0.0268 1.0000
19.250 1.1203 0.11639 0.11115 0.0122 0.0258 1.0000
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Polar data table (+)
Polar graphs
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