GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 596 AIRFOIL (goe596-il) Reynolds number: 50,000 Max Cl/Cd: 37 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe596-il-50000-n5.txt Download as CSV file: xf-goe596-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 596 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 -0.3366 0.11225 0.10491 -0.0304 1.0000 0.1212
-9.250 -0.3476 0.11115 0.10394 -0.0326 1.0000 0.1248
-9.000 -0.3638 0.11037 0.10331 -0.0348 1.0000 0.1257
-8.750 -0.3389 0.10432 0.09723 -0.0324 1.0000 0.1285
-8.500 -0.3310 0.10125 0.09420 -0.0315 1.0000 0.1326
-8.250 -0.3362 0.09934 0.09239 -0.0317 1.0000 0.1380
-8.000 -0.3617 0.09900 0.09227 -0.0325 1.0000 0.1405
-7.750 -0.3447 0.09453 0.08782 -0.0305 1.0000 0.1448
-7.500 -0.3450 0.09229 0.08567 -0.0290 1.0000 0.1500
-7.250 -0.3667 0.09135 0.08491 -0.0298 1.0000 0.1551
-7.000 -0.3739 0.08872 0.08240 -0.0295 1.0000 0.1577
-6.750 -0.3664 0.08582 0.07954 -0.0264 1.0000 0.1616
-6.500 -0.3714 0.08375 0.07755 -0.0253 1.0000 0.1661
-6.000 -0.3845 0.07918 0.07312 -0.0244 1.0000 0.1752
-5.500 -0.3737 0.06702 0.06052 -0.0349 0.9997 0.0928
-5.000 -0.3027 0.05501 0.04742 -0.0504 0.9797 0.0810
-4.750 -0.2721 0.05135 0.04368 -0.0534 0.9712 0.0797
-4.500 -0.2391 0.04771 0.03978 -0.0570 0.9621 0.0782
-4.250 -0.2076 0.04436 0.03608 -0.0598 0.9517 0.0769
-4.000 -0.1738 0.04129 0.03256 -0.0627 0.9421 0.0764
-3.750 -0.1371 0.03860 0.02935 -0.0655 0.9330 0.0779
-3.500 -0.1048 0.03638 0.02664 -0.0671 0.9221 0.0788
-3.250 -0.0671 0.03424 0.02405 -0.0694 0.9139 0.0788
-3.000 -0.0330 0.03248 0.02190 -0.0707 0.9034 0.0790
-2.750 0.0020 0.03095 0.02000 -0.0720 0.8934 0.0795
-2.500 0.0420 0.02961 0.01824 -0.0740 0.8855 0.0810
-2.250 0.0727 0.02842 0.01702 -0.0747 0.8741 0.0843
-2.000 0.1080 0.02744 0.01590 -0.0759 0.8646 0.0876
-1.750 0.1444 0.02650 0.01477 -0.0770 0.8552 0.0901
-1.500 0.1762 0.02582 0.01390 -0.0772 0.8438 0.0927
-1.250 0.2116 0.02512 0.01304 -0.0781 0.8344 0.0962
-1.000 0.2432 0.02451 0.01241 -0.0785 0.8238 0.1037
-0.750 0.2715 0.02407 0.01191 -0.0784 0.8119 0.1134
-0.500 0.3022 0.02357 0.01139 -0.0786 0.8014 0.1264
-0.250 0.3330 0.02286 0.01097 -0.0789 0.7914 0.1668
0.000 0.3865 0.02024 0.01063 -0.0832 0.7818 1.0000
0.250 0.4153 0.02034 0.01038 -0.0829 0.7707 1.0000
0.500 0.4435 0.02043 0.01021 -0.0826 0.7592 1.0000
0.750 0.4679 0.02063 0.01020 -0.0817 0.7463 1.0000
1.000 0.4933 0.02081 0.01020 -0.0810 0.7341 1.0000
1.250 0.5203 0.02094 0.01016 -0.0805 0.7231 1.0000
1.500 0.5476 0.02107 0.01014 -0.0800 0.7125 1.0000
1.750 0.5714 0.02134 0.01031 -0.0791 0.7006 1.0000
2.000 0.5970 0.02157 0.01043 -0.0785 0.6899 1.0000
2.250 0.6256 0.02170 0.01045 -0.0781 0.6808 1.0000
2.500 0.6487 0.02205 0.01075 -0.0773 0.6692 1.0000
2.750 0.6738 0.02235 0.01099 -0.0766 0.6589 1.0000
3.000 0.7021 0.02252 0.01110 -0.0763 0.6498 1.0000
3.250 0.7247 0.02295 0.01153 -0.0753 0.6385 1.0000
3.500 0.7497 0.02330 0.01186 -0.0747 0.6284 1.0000
3.750 0.7769 0.02356 0.01211 -0.0742 0.6189 1.0000
4.000 0.7989 0.02407 0.01266 -0.0733 0.6077 1.0000
4.250 0.8239 0.02446 0.01306 -0.0726 0.5977 1.0000
4.500 0.8495 0.02483 0.01346 -0.0720 0.5876 1.0000
4.750 0.8708 0.02541 0.01412 -0.0710 0.5764 1.0000
5.000 0.8955 0.02583 0.01459 -0.0703 0.5663 1.0000
5.250 0.9198 0.02628 0.01510 -0.0695 0.5558 1.0000
5.500 0.9402 0.02689 0.01585 -0.0683 0.5441 1.0000
5.750 0.9629 0.02733 0.01636 -0.0673 0.5322 1.0000
6.000 0.9872 0.02763 0.01671 -0.0663 0.5201 1.0000
6.250 1.0092 0.02801 0.01720 -0.0651 0.5072 1.0000
6.500 1.0281 0.02858 0.01791 -0.0637 0.4940 1.0000
6.750 1.0477 0.02917 0.01865 -0.0624 0.4819 1.0000
7.000 1.0695 0.02965 0.01927 -0.0612 0.4708 1.0000
7.250 1.0926 0.03005 0.01981 -0.0602 0.4599 1.0000
7.500 1.1102 0.03052 0.02044 -0.0585 0.4455 1.0000
7.750 1.1277 0.03068 0.02068 -0.0564 0.4282 1.0000
8.000 1.1387 0.03103 0.02116 -0.0537 0.4072 1.0000
8.250 1.1522 0.03114 0.02133 -0.0511 0.3855 1.0000
8.500 1.1628 0.03160 0.02184 -0.0484 0.3641 1.0000
8.750 1.1718 0.03217 0.02245 -0.0456 0.3418 1.0000
9.000 1.1775 0.03291 0.02319 -0.0426 0.3171 1.0000
9.250 1.1799 0.03384 0.02410 -0.0393 0.2925 1.0000
9.500 1.1808 0.03509 0.02547 -0.0362 0.2686 1.0000
9.750 1.1798 0.03657 0.02699 -0.0333 0.2413 1.0000
10.000 1.1758 0.03846 0.02880 -0.0307 0.2100 1.0000
10.250 1.1679 0.04090 0.03103 -0.0283 0.1803 1.0000
10.500 1.1587 0.04384 0.03378 -0.0266 0.1559 1.0000
10.750 1.1503 0.04704 0.03687 -0.0253 0.1360 1.0000
11.000 1.1439 0.05028 0.04005 -0.0245 0.1218 1.0000
11.250 1.1397 0.05347 0.04324 -0.0238 0.1119 1.0000
11.500 1.1354 0.05677 0.04648 -0.0234 0.1049 1.0000
11.750 1.1344 0.05982 0.04959 -0.0230 0.0984 1.0000
12.000 1.1321 0.06303 0.05273 -0.0228 0.0936 1.0000
12.250 1.1341 0.06588 0.05574 -0.0224 0.0884 1.0000
12.500 1.1357 0.06874 0.05864 -0.0221 0.0844 1.0000
12.750 1.1399 0.07132 0.06122 -0.0216 0.0811 1.0000
13.000 1.1452 0.07398 0.06411 -0.0212 0.0773 1.0000
13.250 1.1498 0.07668 0.06689 -0.0209 0.0737 1.0000
13.500 1.1607 0.07852 0.06865 -0.0198 0.0704 1.0000
13.750 1.1653 0.08168 0.07212 -0.0197 0.0681 1.0000
14.000 1.1670 0.08521 0.07595 -0.0199 0.0656 1.0000
14.250 1.1681 0.08878 0.07972 -0.0204 0.0633 1.0000
14.500 1.1730 0.09181 0.08285 -0.0204 0.0610 1.0000
14.750 1.1834 0.09446 0.08554 -0.0198 0.0589 1.0000
15.000 1.1705 0.10031 0.09172 -0.0220 0.0583 1.0000
15.250 1.1550 0.10684 0.09855 -0.0250 0.0578 1.0000
15.500 1.1365 0.11428 0.10626 -0.0288 0.0575 1.0000
15.750 1.1153 0.12277 0.11499 -0.0336 0.0575 1.0000
16.000 1.0906 0.13272 0.12516 -0.0395 0.0576 1.0000
16.250 1.0641 0.14417 0.13676 -0.0465 0.0581 1.0000
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Polar data table (+)
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