GOE 559 AIRFOIL (goe559-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 559 AIRFOIL (goe559-il) Reynolds number: 100,000 Max Cl/Cd: 40.4 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe559-il-100000.txt Download as CSV file: xf-goe559-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 559 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3386 0.09445 0.09027 -0.0421 1.0000 0.0388
-8.000 -0.3432 0.09173 0.08766 -0.0437 1.0000 0.0393
-7.750 -0.3477 0.08916 0.08518 -0.0445 1.0000 0.0394
-7.500 -0.3591 0.08659 0.08273 -0.0455 1.0000 0.0396
-7.250 -0.3656 0.08394 0.08014 -0.0463 1.0000 0.0397
-7.000 -0.3728 0.08160 0.07784 -0.0462 1.0000 0.0398
-6.750 -0.3831 0.07969 0.07596 -0.0452 1.0000 0.0400
-6.500 -0.3932 0.07818 0.07447 -0.0429 1.0000 0.0400
-6.250 -0.4113 0.07744 0.07376 -0.0396 0.9999 0.0402
-6.000 -0.3897 0.06975 0.06624 -0.0426 0.9932 0.0438
-5.750 -0.3517 0.06411 0.06034 -0.0520 0.9809 0.0503
-5.500 -0.3202 0.05802 0.05403 -0.0588 0.9674 0.0557
-5.250 -0.2833 0.05445 0.04982 -0.0653 0.9515 0.0658
-5.000 -0.2529 0.04840 0.04372 -0.0698 0.9403 0.0807
-4.750 -0.2221 0.04381 0.03887 -0.0739 0.9275 0.1088
-4.500 -0.1990 0.03981 0.03500 -0.0760 0.9129 0.1694
-3.250 -0.0571 0.02566 0.01944 -0.0775 0.8222 0.2896
-3.000 -0.0063 0.02409 0.01630 -0.0776 0.8039 0.1757
-2.750 0.0331 0.02262 0.01420 -0.0766 0.7872 0.1247
-2.500 0.0686 0.02223 0.01315 -0.0752 0.7712 0.0933
-2.250 0.1008 0.02131 0.01194 -0.0743 0.7564 0.0771
-2.000 0.1309 0.02045 0.01078 -0.0734 0.7425 0.0657
-1.750 0.1572 0.01920 0.00958 -0.0725 0.7296 0.0586
-1.500 0.1824 0.01874 0.00894 -0.0711 0.7176 0.0516
-1.250 0.2049 0.01812 0.00811 -0.0698 0.7071 0.0481
-1.000 0.2302 0.01779 0.00730 -0.0689 0.6977 0.0453
-0.750 0.2551 0.01761 0.00684 -0.0681 0.6876 0.0456
-0.500 0.3693 0.01463 0.00629 -0.0843 0.6762 1.0000
-0.250 0.3924 0.01485 0.00609 -0.0836 0.6687 1.0000
0.000 0.4134 0.01509 0.00616 -0.0828 0.6598 1.0000
0.250 0.4364 0.01534 0.00613 -0.0822 0.6533 1.0000
0.500 0.4582 0.01563 0.00634 -0.0815 0.6458 1.0000
0.750 0.4824 0.01590 0.00645 -0.0811 0.6406 1.0000
1.000 0.5034 0.01624 0.00682 -0.0804 0.6335 1.0000
1.250 0.5274 0.01652 0.00709 -0.0800 0.6281 1.0000
1.500 0.5495 0.01688 0.00751 -0.0794 0.6222 1.0000
1.750 0.5722 0.01723 0.00796 -0.0789 0.6166 1.0000
2.000 0.5901 0.01619 0.00665 -0.0753 0.5798 1.0000
2.250 0.5969 0.01517 0.00518 -0.0697 0.5145 1.0000
2.500 0.6100 0.01510 0.00496 -0.0666 0.4667 1.0000
2.750 0.6200 0.01550 0.00481 -0.0632 0.3570 1.0000
3.000 0.6186 0.01805 0.00617 -0.0589 0.0453 1.0000
3.250 0.6398 0.01850 0.00679 -0.0575 0.0419 1.0000
3.500 0.6602 0.01906 0.00763 -0.0559 0.0419 1.0000
3.750 0.6788 0.01976 0.00861 -0.0540 0.0431 1.0000
4.000 0.6961 0.02056 0.00968 -0.0520 0.0442 1.0000
4.250 0.7130 0.02134 0.01076 -0.0498 0.0456 1.0000
4.500 0.7278 0.02224 0.01192 -0.0473 0.0482 1.0000
4.750 0.7384 0.02331 0.01322 -0.0443 0.0523 1.0000
5.000 0.7388 0.02482 0.01486 -0.0400 0.0551 1.0000
5.250 0.7600 0.02518 0.01541 -0.0379 0.0642 1.0000
5.500 0.7787 0.02568 0.01608 -0.0353 0.0745 1.0000
5.750 0.8001 0.02618 0.01669 -0.0327 0.0883 1.0000
6.000 0.8317 0.02678 0.01728 -0.0313 0.1046 1.0000
6.250 0.8703 0.02658 0.01740 -0.0301 0.1230 1.0000
6.500 0.9223 0.02747 0.01829 -0.0310 0.1373 1.0000
6.750 0.9804 0.02935 0.02016 -0.0328 0.1474 1.0000
7.000 1.0293 0.03344 0.02416 -0.0346 0.1434 1.0000
7.250 1.0501 0.03525 0.02633 -0.0323 0.1368 1.0000
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Polar data table (+)
Polar graphs
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