GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 591 AIRFOIL (goe591-il) Reynolds number: 100,000 Max Cl/Cd: 57.27 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe591-il-100000-n5.txt Download as CSV file: xf-goe591-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 591 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2792 0.10796 0.10332 -0.0378 1.0000 0.0561
-9.000 -0.2880 0.10633 0.10178 -0.0365 1.0000 0.0575
-8.750 -0.3013 0.10468 0.10024 -0.0399 0.9968 0.0598
-8.500 -0.2919 0.10039 0.09596 -0.0478 0.9880 0.0602
-8.000 -0.2567 0.08930 0.08481 -0.0507 0.9788 0.0457
-7.750 -0.2502 0.08384 0.07936 -0.0569 0.9685 0.0425
-7.500 -0.2359 0.08000 0.07551 -0.0617 0.9599 0.0442
-7.250 -0.2203 0.07471 0.07019 -0.0689 0.9502 0.0442
-7.000 -0.2076 0.06951 0.06495 -0.0752 0.9392 0.0440
-6.750 -0.1910 0.06284 0.05816 -0.0834 0.9302 0.0430
-6.500 -0.1736 0.05625 0.05139 -0.0903 0.9207 0.0425
-6.250 -0.1557 0.05220 0.04718 -0.0935 0.9113 0.0442
-6.000 -0.1329 0.04651 0.04117 -0.0983 0.9042 0.0457
-5.750 -0.1176 0.04114 0.03538 -0.1002 0.8940 0.0459
-5.500 -0.0924 0.03585 0.02947 -0.1029 0.8883 0.0473
-5.250 -0.0749 0.03208 0.02498 -0.1027 0.8783 0.0492
-5.000 -0.0454 0.02894 0.02119 -0.1038 0.8733 0.0500
-4.750 -0.0233 0.02729 0.01932 -0.1033 0.8640 0.0509
-4.500 0.0095 0.02600 0.01782 -0.1044 0.8589 0.0530
-4.250 0.0333 0.02498 0.01657 -0.1038 0.8494 0.0554
-4.000 0.0665 0.02345 0.01466 -0.1046 0.8441 0.0571
-3.750 0.0910 0.02238 0.01331 -0.1038 0.8347 0.0584
-3.500 0.1244 0.02125 0.01188 -0.1045 0.8291 0.0600
-3.250 0.1486 0.02047 0.01104 -0.1038 0.8194 0.0618
-3.000 0.1797 0.01986 0.01037 -0.1043 0.8128 0.0658
-2.750 0.2052 0.01935 0.00975 -0.1036 0.8033 0.0701
-2.500 0.2340 0.01870 0.00898 -0.1035 0.7957 0.0739
-2.250 0.2599 0.01818 0.00847 -0.1030 0.7867 0.0792
-2.000 0.2864 0.01771 0.00793 -0.1025 0.7780 0.0884
-1.750 0.3137 0.01725 0.00746 -0.1022 0.7694 0.1040
-1.500 0.3386 0.01694 0.00724 -0.1015 0.7597 0.1282
-1.250 0.3677 0.01662 0.00699 -0.1016 0.7519 0.1656
-1.000 0.3918 0.01639 0.00689 -0.1008 0.7412 0.2155
-0.750 0.4187 0.01595 0.00673 -0.1007 0.7321 0.2972
-0.500 0.4410 0.01508 0.00664 -0.0997 0.7229 0.5307
-0.250 0.5155 0.01416 0.00647 -0.1081 0.7131 1.0000
0.250 0.5644 0.01433 0.00626 -0.1064 0.6931 1.0000
0.500 0.5879 0.01445 0.00623 -0.1055 0.6824 1.0000
0.750 0.6131 0.01455 0.00616 -0.1048 0.6729 1.0000
1.000 0.6371 0.01468 0.00615 -0.1039 0.6623 1.0000
1.250 0.6607 0.01482 0.00619 -0.1030 0.6516 1.0000
1.500 0.6856 0.01496 0.00619 -0.1022 0.6419 1.0000
1.750 0.7099 0.01511 0.00623 -0.1014 0.6316 1.0000
2.000 0.7334 0.01529 0.00632 -0.1005 0.6208 1.0000
2.250 0.7581 0.01545 0.00639 -0.0998 0.6111 1.0000
2.500 0.7824 0.01563 0.00648 -0.0991 0.6010 1.0000
2.750 0.8057 0.01584 0.00663 -0.0981 0.5902 1.0000
3.000 0.8299 0.01604 0.00675 -0.0974 0.5802 1.0000
3.250 0.8540 0.01625 0.00687 -0.0966 0.5700 1.0000
3.500 0.8768 0.01649 0.00708 -0.0956 0.5590 1.0000
3.750 0.9006 0.01672 0.00727 -0.0948 0.5491 1.0000
4.000 0.9245 0.01696 0.00745 -0.0941 0.5396 1.0000
4.250 0.9471 0.01724 0.00772 -0.0931 0.5296 1.0000
4.500 0.9711 0.01750 0.00795 -0.0924 0.5209 1.0000
4.750 0.9938 0.01779 0.00826 -0.0915 0.5116 1.0000
5.000 1.0170 0.01810 0.00856 -0.0907 0.5029 1.0000
5.250 1.0402 0.01840 0.00886 -0.0899 0.4943 1.0000
5.500 1.0624 0.01873 0.00924 -0.0890 0.4853 1.0000
6.000 1.1069 0.01940 0.00997 -0.0871 0.4675 1.0000
6.250 1.1289 0.01974 0.01033 -0.0861 0.4584 1.0000
6.500 1.1499 0.02008 0.01070 -0.0850 0.4485 1.0000
6.750 1.1694 0.02046 0.01114 -0.0836 0.4375 1.0000
7.000 1.1889 0.02082 0.01155 -0.0822 0.4265 1.0000
7.250 1.2080 0.02119 0.01192 -0.0808 0.4153 1.0000
7.500 1.2254 0.02160 0.01241 -0.0791 0.4035 1.0000
7.750 1.2433 0.02203 0.01294 -0.0776 0.3930 1.0000
8.000 1.2615 0.02248 0.01344 -0.0760 0.3834 1.0000
8.250 1.2782 0.02295 0.01401 -0.0743 0.3731 1.0000
8.500 1.2945 0.02345 0.01462 -0.0726 0.3632 1.0000
8.750 1.3102 0.02396 0.01519 -0.0708 0.3534 1.0000
9.000 1.3216 0.02448 0.01578 -0.0682 0.3416 1.0000
9.250 1.3297 0.02507 0.01644 -0.0652 0.3276 1.0000
9.500 1.3361 0.02574 0.01714 -0.0621 0.3125 1.0000
9.750 1.3430 0.02651 0.01795 -0.0593 0.2982 1.0000
10.000 1.3490 0.02739 0.01886 -0.0565 0.2837 1.0000
10.250 1.3542 0.02838 0.01988 -0.0539 0.2692 1.0000
10.500 1.3564 0.02957 0.02105 -0.0511 0.2530 1.0000
10.750 1.3593 0.03087 0.02237 -0.0486 0.2381 1.0000
11.000 1.3617 0.03230 0.02384 -0.0463 0.2237 1.0000
11.250 1.3628 0.03393 0.02552 -0.0441 0.2089 1.0000
11.500 1.3620 0.03579 0.02741 -0.0421 0.1930 1.0000
11.750 1.3607 0.03785 0.02949 -0.0403 0.1742 1.0000
12.000 1.3570 0.04022 0.03186 -0.0387 0.1559 1.0000
12.500 1.3413 0.04623 0.03777 -0.0360 0.1205 1.0000
12.750 1.3306 0.04982 0.04131 -0.0351 0.0999 1.0000
13.250 1.2987 0.05887 0.05010 -0.0345 0.0541 1.0000
13.500 1.2857 0.06344 0.05469 -0.0346 0.0439 1.0000
13.750 1.2749 0.06798 0.05929 -0.0350 0.0366 1.0000
14.000 1.2649 0.07258 0.06399 -0.0357 0.0328 1.0000
14.250 1.2551 0.07735 0.06888 -0.0366 0.0302 1.0000
14.500 1.2450 0.08235 0.07399 -0.0378 0.0287 1.0000
14.750 1.2346 0.08756 0.07932 -0.0392 0.0275 1.0000
15.000 1.2250 0.09276 0.08469 -0.0407 0.0267 1.0000
15.250 1.2159 0.09804 0.09015 -0.0424 0.0260 1.0000
15.500 1.2062 0.10353 0.09579 -0.0443 0.0253 1.0000
15.750 1.1966 0.10908 0.10148 -0.0463 0.0246 1.0000
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Polar data table (+)
Polar graphs
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