GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il) Reynolds number: 100,000 Max Cl/Cd: 51.48 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe182-il-100000-n5.txt Download as CSV file: xf-goe182-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 182 (MVA H.27) 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 -0.3068 0.10709 0.10226 -0.0209 1.0000 0.0564
-8.500 -0.3106 0.10522 0.10047 -0.0243 1.0000 0.0569
-8.250 -0.3136 0.10303 0.09837 -0.0269 1.0000 0.0571
-8.000 -0.2914 0.09738 0.09271 -0.0233 1.0000 0.0586
-7.750 -0.2838 0.09453 0.08990 -0.0230 1.0000 0.0598
-7.500 -0.2802 0.09203 0.08746 -0.0230 1.0000 0.0610
-7.250 -0.2796 0.08974 0.08525 -0.0229 1.0000 0.0621
-7.000 -0.2788 0.08736 0.08295 -0.0233 1.0000 0.0633
-6.750 -0.2792 0.08515 0.08081 -0.0248 1.0000 0.0657
-6.500 -0.2808 0.08291 0.07866 -0.0327 1.0000 0.0678
-6.250 -0.2589 0.07789 0.07364 -0.0406 0.9944 0.0684
-5.750 -0.1985 0.06614 0.06172 -0.0518 0.9762 0.0563
-5.500 -0.1582 0.06014 0.05558 -0.0621 0.9650 0.0565
-5.250 -0.1253 0.05577 0.05113 -0.0675 0.9531 0.0557
-5.000 -0.0899 0.05106 0.04629 -0.0739 0.9391 0.0544
-4.750 -0.0503 0.04552 0.04050 -0.0818 0.9223 0.0541
-4.500 -0.0075 0.03908 0.03363 -0.0901 0.9034 0.0553
-4.250 0.0306 0.03391 0.02798 -0.0952 0.8828 0.0549
-4.000 0.0665 0.02958 0.02304 -0.0988 0.8594 0.0550
-3.750 0.1017 0.02634 0.01905 -0.1010 0.8361 0.0564
-3.500 0.1325 0.02439 0.01664 -0.1018 0.8119 0.0581
-3.250 0.1618 0.02296 0.01484 -0.1020 0.7885 0.0591
-3.000 0.1903 0.02175 0.01324 -0.1019 0.7655 0.0600
-2.750 0.2186 0.02074 0.01186 -0.1016 0.7441 0.0612
-2.500 0.2465 0.01989 0.01068 -0.1013 0.7233 0.0627
-2.250 0.2742 0.01921 0.00970 -0.1009 0.7034 0.0652
-2.000 0.3019 0.01873 0.00889 -0.1004 0.6842 0.0682
-1.750 0.3287 0.01804 0.00814 -0.1001 0.6654 0.0710
-1.500 0.3557 0.01755 0.00754 -0.0996 0.6463 0.0738
-1.250 0.3827 0.01713 0.00697 -0.0991 0.6263 0.0774
-1.000 0.4095 0.01674 0.00646 -0.0986 0.6062 0.0820
-0.750 0.4361 0.01646 0.00610 -0.0981 0.5860 0.0906
-0.500 0.4630 0.01623 0.00581 -0.0977 0.5654 0.1011
-0.250 0.4895 0.01610 0.00562 -0.0972 0.5450 0.1182
0.000 0.5161 0.01600 0.00550 -0.0967 0.5251 0.1518
0.250 0.5432 0.01588 0.00541 -0.0964 0.5060 0.2067
0.500 0.5701 0.01580 0.00541 -0.0961 0.4870 0.2767
0.750 0.5965 0.01566 0.00546 -0.0958 0.4687 0.3704
1.000 0.6202 0.01514 0.00552 -0.0949 0.4514 0.5942
1.250 0.6496 0.01475 0.00543 -0.0948 0.4336 1.0000
1.500 0.6761 0.01503 0.00548 -0.0943 0.4178 1.0000
1.750 0.7023 0.01533 0.00556 -0.0939 0.4034 1.0000
2.000 0.7285 0.01565 0.00568 -0.0935 0.3906 1.0000
2.250 0.7544 0.01599 0.00582 -0.0930 0.3792 1.0000
2.500 0.7807 0.01631 0.00601 -0.0926 0.3688 1.0000
2.750 0.8066 0.01666 0.00621 -0.0922 0.3603 1.0000
3.000 0.8327 0.01702 0.00645 -0.0918 0.3523 1.0000
3.250 0.8585 0.01740 0.00670 -0.0914 0.3460 1.0000
3.500 0.8847 0.01775 0.00701 -0.0910 0.3398 1.0000
3.750 0.9105 0.01816 0.00732 -0.0906 0.3349 1.0000
4.000 0.9365 0.01856 0.00765 -0.0902 0.3305 1.0000
4.250 0.9626 0.01896 0.00804 -0.0899 0.3260 1.0000
4.500 0.9885 0.01938 0.00843 -0.0895 0.3222 1.0000
4.750 1.0142 0.01983 0.00882 -0.0892 0.3191 1.0000
5.000 1.0402 0.02030 0.00926 -0.0888 0.3162 1.0000
5.250 1.0661 0.02075 0.00978 -0.0885 0.3132 1.0000
5.500 1.0919 0.02122 0.01029 -0.0882 0.3104 1.0000
5.750 1.1177 0.02171 0.01081 -0.0879 0.3080 1.0000
6.000 1.1434 0.02223 0.01136 -0.0875 0.3058 1.0000
6.250 1.1692 0.02276 0.01191 -0.0872 0.3039 1.0000
6.500 1.1950 0.02334 0.01248 -0.0870 0.3021 1.0000
6.750 1.2201 0.02390 0.01319 -0.0866 0.3000 1.0000
7.000 1.2450 0.02448 0.01394 -0.0862 0.2977 1.0000
7.250 1.2697 0.02508 0.01467 -0.0858 0.2955 1.0000
7.500 1.2943 0.02569 0.01540 -0.0854 0.2933 1.0000
7.750 1.3189 0.02630 0.01614 -0.0850 0.2912 1.0000
8.000 1.3435 0.02690 0.01681 -0.0846 0.2889 1.0000
8.250 1.3680 0.02747 0.01742 -0.0842 0.2858 1.0000
8.500 1.3890 0.02808 0.01832 -0.0834 0.2816 1.0000
8.750 1.4109 0.02862 0.01907 -0.0826 0.2773 1.0000
9.000 1.4338 0.02912 0.01967 -0.0820 0.2736 1.0000
9.250 1.4579 0.02965 0.02023 -0.0815 0.2705 1.0000
9.500 1.4764 0.03034 0.02128 -0.0804 0.2662 1.0000
9.750 1.4951 0.03068 0.02181 -0.0792 0.2590 1.0000
10.000 1.5115 0.03084 0.02213 -0.0777 0.2491 1.0000
10.250 1.5269 0.03087 0.02220 -0.0760 0.2377 1.0000
10.500 1.5391 0.03136 0.02302 -0.0741 0.2257 1.0000
10.750 1.5518 0.03190 0.02379 -0.0723 0.2133 1.0000
11.000 1.5619 0.03256 0.02468 -0.0703 0.1948 1.0000
11.250 1.5578 0.03385 0.02575 -0.0670 0.1284 1.0000
11.500 1.5382 0.03699 0.02859 -0.0632 0.1045 1.0000
11.750 1.5225 0.04047 0.03210 -0.0608 0.0776 1.0000
12.000 1.5022 0.04490 0.03656 -0.0596 0.0672 1.0000
12.250 1.4825 0.04996 0.04173 -0.0598 0.0631 1.0000
12.500 1.4610 0.05588 0.04782 -0.0611 0.0607 1.0000
12.750 1.4374 0.06267 0.05481 -0.0633 0.0596 1.0000
13.000 1.4119 0.07026 0.06263 -0.0661 0.0595 1.0000
13.250 1.3857 0.07822 0.07081 -0.0691 0.0597 1.0000
13.500 1.3600 0.08624 0.07903 -0.0720 0.0598 1.0000
13.750 1.3354 0.09405 0.08697 -0.0747 0.0595 1.0000
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Polar data table (+)
Polar graphs
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