GOE 178 AIRFOIL (goe178-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 178 AIRFOIL (goe178-il) Reynolds number: 100,000 Max Cl/Cd: 58.62 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe178-il-100000-n5.txt Download as CSV file: xf-goe178-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 178 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3693 0.10795 0.10315 -0.0157 1.0000 0.0536
-8.500 -0.3726 0.10585 0.10113 -0.0203 1.0000 0.0545
-8.250 -0.3737 0.10316 0.09853 -0.0238 1.0000 0.0548
-8.000 -0.3712 0.09990 0.09533 -0.0275 1.0000 0.0549
-7.750 -0.3566 0.09460 0.09003 -0.0228 1.0000 0.0561
-7.500 -0.3482 0.09138 0.08683 -0.0224 1.0000 0.0573
-7.250 -0.3421 0.08856 0.08406 -0.0228 1.0000 0.0593
-7.000 -0.3367 0.08576 0.08129 -0.0255 1.0000 0.0631
-6.750 -0.3307 0.08260 0.07820 -0.0367 1.0000 0.0659
-6.500 -0.3211 0.07870 0.07429 -0.0419 1.0000 0.0661
-6.000 -0.3130 0.06662 0.06223 -0.0418 1.0000 0.0456
-5.750 -0.3007 0.06209 0.05763 -0.0450 1.0000 0.0437
-5.000 -0.1842 0.04220 0.03687 -0.0710 0.9770 0.0454
-4.750 -0.1497 0.04073 0.03532 -0.0741 0.9679 0.0485
-4.500 -0.1090 0.03536 0.02947 -0.0799 0.9582 0.0489
-4.250 -0.0694 0.03063 0.02414 -0.0844 0.9480 0.0489
-4.000 -0.0328 0.02733 0.02030 -0.0873 0.9353 0.0499
-3.750 0.0010 0.02496 0.01740 -0.0889 0.9191 0.0525
-3.500 0.0333 0.02281 0.01477 -0.0899 0.9003 0.0531
-3.250 0.0663 0.02104 0.01257 -0.0908 0.8807 0.0536
-3.000 0.0988 0.01963 0.01077 -0.0913 0.8598 0.0544
-2.750 0.1298 0.01853 0.00943 -0.0915 0.8372 0.0555
-2.500 0.1589 0.01780 0.00855 -0.0913 0.8127 0.0570
-2.250 0.1868 0.01722 0.00778 -0.0909 0.7867 0.0591
-2.000 0.2139 0.01676 0.00713 -0.0903 0.7591 0.0625
-1.750 0.2407 0.01640 0.00659 -0.0897 0.7305 0.0678
-1.500 0.2675 0.01608 0.00614 -0.0892 0.7025 0.0736
-1.250 0.2947 0.01571 0.00559 -0.0887 0.6769 0.0813
-1.000 0.3217 0.01545 0.00516 -0.0883 0.6541 0.0951
-0.750 0.3488 0.01525 0.00485 -0.0879 0.6334 0.1125
-0.500 0.3758 0.01515 0.00468 -0.0877 0.6154 0.1364
-0.250 0.4030 0.01510 0.00456 -0.0874 0.6001 0.1561
0.000 0.4306 0.01503 0.00449 -0.0873 0.5870 0.1991
0.250 0.4579 0.01454 0.00453 -0.0876 0.5761 0.3797
0.750 0.5080 0.01343 0.00446 -0.0855 0.5566 1.0000
1.000 0.5357 0.01367 0.00448 -0.0854 0.5484 1.0000
1.250 0.5635 0.01389 0.00456 -0.0854 0.5403 1.0000
1.500 0.5912 0.01414 0.00465 -0.0853 0.5333 1.0000
1.750 0.6188 0.01438 0.00477 -0.0852 0.5254 1.0000
2.000 0.6463 0.01464 0.00490 -0.0851 0.5176 1.0000
2.250 0.6735 0.01488 0.00504 -0.0849 0.5083 1.0000
2.500 0.7007 0.01512 0.00521 -0.0848 0.4990 1.0000
2.750 0.7278 0.01539 0.00537 -0.0846 0.4913 1.0000
3.000 0.7552 0.01564 0.00563 -0.0845 0.4841 1.0000
3.250 0.7825 0.01593 0.00587 -0.0844 0.4781 1.0000
3.500 0.8097 0.01622 0.00615 -0.0843 0.4722 1.0000
3.750 0.8369 0.01650 0.00647 -0.0842 0.4657 1.0000
4.000 0.8639 0.01682 0.00674 -0.0841 0.4602 1.0000
4.250 0.8909 0.01711 0.00713 -0.0840 0.4533 1.0000
4.500 0.9178 0.01743 0.00747 -0.0838 0.4474 1.0000
4.750 0.9444 0.01774 0.00787 -0.0836 0.4404 1.0000
5.000 0.9707 0.01803 0.00819 -0.0834 0.4322 1.0000
5.250 0.9966 0.01831 0.00856 -0.0831 0.4222 1.0000
5.500 1.0224 0.01858 0.00890 -0.0827 0.4126 1.0000
5.750 1.0481 0.01885 0.00928 -0.0824 0.4028 1.0000
6.000 1.0738 0.01915 0.00973 -0.0821 0.3935 1.0000
6.250 1.0993 0.01945 0.01012 -0.0817 0.3853 1.0000
6.500 1.1238 0.01966 0.01047 -0.0811 0.3708 1.0000
6.750 1.1478 0.01982 0.01079 -0.0805 0.3490 1.0000
7.000 1.1716 0.02006 0.01113 -0.0799 0.3287 1.0000
7.250 1.1952 0.02039 0.01157 -0.0793 0.3046 1.0000
7.500 1.2133 0.02110 0.01200 -0.0780 0.2490 1.0000
7.750 1.2294 0.02238 0.01301 -0.0768 0.1928 1.0000
8.000 1.2278 0.02584 0.01547 -0.0742 0.0615 1.0000
8.250 1.2395 0.02765 0.01736 -0.0723 0.0439 1.0000
8.500 1.2528 0.02914 0.01895 -0.0707 0.0338 1.0000
8.750 1.2657 0.03055 0.02054 -0.0690 0.0294 1.0000
9.250 1.2815 0.03388 0.02421 -0.0650 0.0256 1.0000
9.500 1.2839 0.03563 0.02616 -0.0624 0.0241 1.0000
9.750 1.2838 0.03760 0.02828 -0.0601 0.0229 1.0000
10.000 1.2816 0.03992 0.03074 -0.0582 0.0218 1.0000
10.250 1.2769 0.04274 0.03371 -0.0569 0.0210 1.0000
10.500 1.2705 0.04606 0.03717 -0.0562 0.0205 1.0000
10.750 1.2638 0.04966 0.04089 -0.0559 0.0201 1.0000
11.000 1.2603 0.05300 0.04434 -0.0555 0.0198 1.0000
11.250 1.2603 0.05595 0.04742 -0.0549 0.0196 1.0000
11.500 1.2628 0.05855 0.05011 -0.0539 0.0192 1.0000
11.750 1.2684 0.06076 0.05242 -0.0524 0.0189 1.0000
12.000 1.2762 0.06283 0.05460 -0.0508 0.0184 1.0000
12.250 1.2834 0.06513 0.05709 -0.0495 0.0178 1.0000
12.500 1.2890 0.06775 0.05988 -0.0486 0.0171 1.0000
12.750 1.2926 0.07069 0.06299 -0.0480 0.0165 1.0000
13.000 1.2950 0.07387 0.06635 -0.0476 0.0160 1.0000
13.250 1.2963 0.07731 0.06999 -0.0472 0.0158 1.0000
13.500 1.2953 0.08114 0.07404 -0.0473 0.0156 1.0000
13.750 1.2914 0.08541 0.07853 -0.0478 0.0155 1.0000
14.000 1.2847 0.09010 0.08346 -0.0488 0.0154 1.0000
14.250 1.2756 0.09524 0.08884 -0.0503 0.0154 1.0000
14.500 1.2647 0.10078 0.09461 -0.0523 0.0154 1.0000
14.750 1.2522 0.10679 0.10084 -0.0549 0.0154 1.0000
15.000 1.2383 0.11330 0.10758 -0.0581 0.0154 1.0000
15.250 1.2228 0.12047 0.11497 -0.0620 0.0155 1.0000
15.500 1.2061 0.12828 0.12301 -0.0666 0.0156 1.0000
15.750 1.1885 0.13684 0.13178 -0.0720 0.0158 1.0000
16.000 1.1697 0.14643 0.14156 -0.0783 0.0160 1.0000
16.250 1.1494 0.15739 0.15268 -0.0857 0.0162 1.0000
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Polar data table (+)
Polar graphs
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