GOE 16K AIRFOIL (goe16k-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 16K AIRFOIL (goe16k-il) Reynolds number: 500,000 Max Cl/Cd: 69.19 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe16k-il-500000.txt Download as CSV file: xf-goe16k-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 16K 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
------ -------- --------- --------- -------- -------- --------
-18.250 -0.5631 0.09688 0.09369 -0.1463 0.9464 0.0336
-18.000 -0.6319 0.08216 0.07866 -0.1553 0.9456 0.0334
-17.750 -0.6630 0.07363 0.06992 -0.1613 0.9449 0.0335
-17.250 -0.6991 0.06065 0.05653 -0.1714 0.9436 0.0343
-17.000 -0.7252 0.05705 0.05284 -0.1693 0.9366 0.0344
-16.750 -0.7118 0.05537 0.05120 -0.1713 0.9352 0.0351
-16.500 -0.7231 0.05075 0.04638 -0.1738 0.9338 0.0350
-16.250 -0.7120 0.04884 0.04444 -0.1758 0.9329 0.0357
-16.000 -0.7055 0.04652 0.04204 -0.1777 0.9321 0.0365
-15.750 -0.7008 0.04425 0.03965 -0.1792 0.9314 0.0371
-15.500 -0.7224 0.04267 0.03796 -0.1743 0.9238 0.0375
-15.250 -0.7231 0.04057 0.03571 -0.1736 0.9220 0.0379
-15.000 -0.7251 0.03874 0.03365 -0.1726 0.9206 0.0388
-14.750 -0.7222 0.03675 0.03148 -0.1718 0.9197 0.0393
-14.500 -0.7101 0.03516 0.02984 -0.1716 0.9190 0.0398
-14.250 -0.6940 0.03420 0.02888 -0.1716 0.9185 0.0406
-14.000 -0.7106 0.03399 0.02865 -0.1645 0.9104 0.0410
-13.750 -0.7021 0.03287 0.02743 -0.1629 0.9088 0.0414
-13.500 -0.6914 0.03220 0.02668 -0.1613 0.9076 0.0424
-13.250 -0.6801 0.03124 0.02559 -0.1598 0.9067 0.0432
-13.000 -0.6710 0.03044 0.02462 -0.1578 0.9059 0.0444
-12.750 -0.6561 0.02956 0.02361 -0.1567 0.9053 0.0447
-12.500 -0.6748 0.02957 0.02352 -0.1483 0.8979 0.0449
-12.250 -0.6606 0.02837 0.02233 -0.1470 0.8959 0.0463
-12.000 -0.6451 0.02768 0.02161 -0.1455 0.8946 0.0470
-11.750 -0.6292 0.02711 0.02099 -0.1442 0.8935 0.0479
-11.500 -0.6124 0.02655 0.02035 -0.1428 0.8926 0.0490
-11.250 -0.5937 0.02593 0.01963 -0.1418 0.8918 0.0501
-11.000 -0.5739 0.02539 0.01897 -0.1410 0.8912 0.0509
-10.750 -0.6057 0.02613 0.01964 -0.1291 0.8829 0.0513
-10.500 -0.5920 0.02534 0.01875 -0.1269 0.8807 0.0521
-10.250 -0.5662 0.02431 0.01773 -0.1275 0.8798 0.0532
-10.000 -0.5474 0.02393 0.01734 -0.1262 0.8787 0.0543
-9.750 -0.5264 0.02347 0.01684 -0.1254 0.8779 0.0553
-9.500 -0.5025 0.02287 0.01617 -0.1252 0.8772 0.0565
-9.250 -0.4789 0.02242 0.01564 -0.1249 0.8765 0.0578
-9.000 -0.5478 0.02421 0.01742 -0.1051 0.8646 0.0571
-8.750 -0.5312 0.02393 0.01709 -0.1032 0.8633 0.0579
-8.500 -0.5114 0.02365 0.01672 -0.1018 0.8624 0.0589
-8.250 -0.4852 0.02311 0.01611 -0.1019 0.8618 0.0593
-8.000 -0.5727 0.02561 0.01860 -0.0788 0.8489 0.0589
-7.750 -0.5504 0.02504 0.01798 -0.0781 0.8479 0.0600
-7.500 -0.5247 0.02430 0.01724 -0.0782 0.8471 0.0613
-7.250 -0.5027 0.02396 0.01690 -0.0774 0.8463 0.0628
-7.000 -0.4809 0.02366 0.01658 -0.0764 0.8456 0.0638
-6.750 -0.5241 0.02518 0.01807 -0.0625 0.8386 0.0639
-6.500 -0.4777 0.02435 0.01720 -0.0664 0.8404 0.0656
-6.250 -0.4387 0.02373 0.01653 -0.0689 0.8413 0.0670
-6.000 -0.4021 0.02317 0.01592 -0.0710 0.8419 0.0681
-5.750 -0.3685 0.02233 0.01508 -0.0724 0.8423 0.0702
-2.750 -0.2798 0.02489 0.01755 -0.0266 0.8009 0.0985
-2.500 -0.2479 0.02440 0.01742 -0.0280 0.7997 0.1632
-2.250 -0.2172 0.02405 0.01735 -0.0290 0.7988 0.2233
-2.000 -0.1876 0.02386 0.01729 -0.0296 0.7979 0.2576
-1.750 -0.1572 0.02366 0.01722 -0.0304 0.7972 0.2895
-1.500 -0.1265 0.02348 0.01715 -0.0313 0.7966 0.3211
-1.250 -0.0954 0.02329 0.01708 -0.0322 0.7961 0.3506
-1.000 -0.0638 0.02310 0.01698 -0.0332 0.7957 0.3789
-0.750 -0.0328 0.02287 0.01687 -0.0340 0.7952 0.4135
-0.500 -0.0027 0.02259 0.01678 -0.0348 0.7947 0.4579
-0.250 0.1654 0.02398 0.02003 -0.0664 0.7968 0.8960
0.000 0.1898 0.02402 0.02004 -0.0654 0.7961 0.9141
0.250 0.2401 0.02449 0.02048 -0.0696 0.7958 0.9332
0.750 0.2730 0.02662 0.02259 -0.0661 0.7840 0.9489
1.000 0.3325 0.02715 0.02311 -0.0728 0.7839 0.9555
1.250 0.3773 0.02724 0.02318 -0.0766 0.7833 0.9596
1.500 0.4175 0.02722 0.02314 -0.0792 0.7828 0.9642
1.750 0.4694 0.02725 0.02318 -0.0847 0.7826 0.9670
2.000 0.5147 0.02716 0.02308 -0.0885 0.7823 0.9716
2.250 0.5645 0.02681 0.02273 -0.0932 0.7821 0.9757
2.500 0.6129 0.02657 0.02250 -0.0979 0.7819 0.9792
2.750 0.6805 0.02620 0.02217 -0.1067 0.7824 0.9878
3.000 0.8105 0.02295 0.01891 -0.1269 0.7959 0.9927
3.250 0.8635 0.02177 0.01773 -0.1320 0.7962 0.9936
3.500 0.9204 0.02053 0.01651 -0.1382 0.7963 0.9949
3.750 0.9221 0.02080 0.01681 -0.1334 0.7880 0.9982
4.000 1.1006 0.01653 0.01242 -0.1644 0.7940 0.9942
4.250 1.0507 0.01735 0.01333 -0.1482 0.7834 0.9990
4.500 1.1080 0.01623 0.01221 -0.1545 0.7803 0.9993
4.750 1.1208 0.01620 0.01219 -0.1516 0.7751 0.9996
8.000 1.0580 0.02514 0.01990 -0.0711 0.4408 1.0000
8.250 1.0529 0.02638 0.02096 -0.0658 0.4104 1.0000
8.500 1.0550 0.02734 0.02182 -0.0619 0.3888 1.0000
8.750 1.0602 0.02818 0.02257 -0.0585 0.3638 1.0000
9.000 1.0617 0.02925 0.02350 -0.0545 0.3327 1.0000
9.250 1.0663 0.03019 0.02431 -0.0512 0.3038 1.0000
9.500 1.0638 0.03153 0.02541 -0.0469 0.2584 1.0000
9.750 1.0662 0.03265 0.02635 -0.0435 0.2262 1.0000
10.000 1.0697 0.03373 0.02725 -0.0402 0.1972 1.0000
10.250 1.0784 0.03454 0.02799 -0.0377 0.1807 1.0000
10.500 1.0865 0.03542 0.02878 -0.0353 0.1637 1.0000
10.750 1.0950 0.03629 0.02957 -0.0329 0.1479 1.0000
11.000 1.1057 0.03706 0.03031 -0.0308 0.1383 1.0000
11.250 1.1167 0.03781 0.03104 -0.0289 0.1283 1.0000
11.500 1.1264 0.03866 0.03185 -0.0267 0.1170 1.0000
11.750 1.1354 0.03959 0.03272 -0.0246 0.1078 1.0000
12.000 1.1463 0.04040 0.03354 -0.0227 0.1010 1.0000
12.250 1.1558 0.04131 0.03443 -0.0207 0.0949 1.0000
12.500 1.1665 0.04215 0.03528 -0.0189 0.0886 1.0000
12.750 1.1744 0.04320 0.03632 -0.0168 0.0834 1.0000
13.000 1.1855 0.04406 0.03720 -0.0151 0.0778 1.0000
13.250 1.1926 0.04519 0.03830 -0.0131 0.0732 1.0000
13.500 1.2043 0.04604 0.03920 -0.0115 0.0691 1.0000
13.750 1.2102 0.04731 0.04043 -0.0094 0.0641 1.0000
14.000 1.2206 0.04828 0.04147 -0.0078 0.0610 1.0000
14.250 1.2289 0.04941 0.04258 -0.0062 0.0569 1.0000
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