GOE 336 (MVA H.44) AIRFOIL (goe336-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 336 (MVA H.44) AIRFOIL (goe336-il) Reynolds number: 100,000 Max Cl/Cd: 57.8 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe336-il-100000-n5.txt Download as CSV file: xf-goe336-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 336 (MVA H.44) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2860 0.09452 0.09006 -0.0293 1.0000 0.0536
-7.500 -0.2964 0.09318 0.08885 -0.0288 1.0000 0.0555
-7.250 -0.2936 0.09155 0.08726 -0.0374 0.9914 0.0571
-6.750 -0.2509 0.08124 0.07693 -0.0453 0.9675 0.0588
-6.500 -0.2297 0.07729 0.07294 -0.0473 0.9535 0.0606
-6.250 -0.2057 0.07368 0.06927 -0.0516 0.9370 0.0645
-6.000 -0.1630 0.07112 0.06631 -0.0662 0.9141 0.0694
-5.750 -0.1444 0.06587 0.06103 -0.0679 0.8980 0.0700
-5.500 -0.1271 0.06177 0.05691 -0.0681 0.8811 0.0710
-5.250 -0.1067 0.05842 0.05346 -0.0692 0.8631 0.0721
-5.000 -0.0863 0.05571 0.05063 -0.0699 0.8452 0.0752
-4.500 -0.0318 0.04655 0.04074 -0.0758 0.8130 0.0561
-4.250 -0.0104 0.04374 0.03773 -0.0761 0.7979 0.0546
-4.000 0.0134 0.04085 0.03456 -0.0767 0.7840 0.0535
-3.750 0.0391 0.03809 0.03145 -0.0772 0.7709 0.0549
-3.500 0.0639 0.03548 0.02850 -0.0774 0.7585 0.0546
-3.250 0.0889 0.03297 0.02564 -0.0773 0.7470 0.0536
-3.000 0.1143 0.03053 0.02281 -0.0770 0.7358 0.0529
-2.750 0.1399 0.02825 0.02014 -0.0767 0.7246 0.0525
-2.500 0.1660 0.02624 0.01770 -0.0762 0.7146 0.0525
-2.250 0.1924 0.02459 0.01562 -0.0757 0.7046 0.0535
-2.000 0.2192 0.02320 0.01381 -0.0752 0.6941 0.0557
-1.750 0.2464 0.02194 0.01215 -0.0748 0.6844 0.0565
-1.500 0.2736 0.02088 0.01076 -0.0743 0.6745 0.0569
-1.250 0.3008 0.02001 0.00967 -0.0739 0.6644 0.0576
-1.000 0.3277 0.01936 0.00890 -0.0736 0.6558 0.0589
-0.750 0.3545 0.01888 0.00836 -0.0733 0.6463 0.0606
-0.500 0.3816 0.01847 0.00785 -0.0730 0.6382 0.0629
-0.250 0.4085 0.01808 0.00737 -0.0726 0.6298 0.0663
0.000 0.4352 0.01779 0.00703 -0.0722 0.6220 0.0718
0.250 0.4623 0.01762 0.00682 -0.0719 0.6142 0.0823
0.500 0.4905 0.01740 0.00655 -0.0718 0.6069 0.0977
0.750 0.5185 0.01724 0.00639 -0.0718 0.5997 0.1187
1.000 0.5454 0.01720 0.00631 -0.0716 0.5939 0.1435
1.250 0.5718 0.01717 0.00636 -0.0714 0.5873 0.1707
1.500 0.5981 0.01709 0.00638 -0.0711 0.5821 0.2128
1.750 0.6195 0.01626 0.00644 -0.0702 0.5768 0.5211
2.000 0.7012 0.01578 0.00654 -0.0814 0.5696 1.0000
2.250 0.7267 0.01598 0.00658 -0.0809 0.5652 1.0000
2.500 0.7515 0.01623 0.00679 -0.0803 0.5595 1.0000
2.750 0.7766 0.01647 0.00696 -0.0798 0.5545 1.0000
3.000 0.8020 0.01669 0.00707 -0.0792 0.5503 1.0000
3.250 0.8262 0.01696 0.00734 -0.0786 0.5442 1.0000
3.500 0.8509 0.01718 0.00753 -0.0780 0.5382 1.0000
3.750 0.8756 0.01742 0.00771 -0.0774 0.5326 1.0000
4.000 0.8996 0.01769 0.00801 -0.0767 0.5264 1.0000
4.250 0.9244 0.01794 0.00825 -0.0761 0.5215 1.0000
4.500 0.9485 0.01821 0.00855 -0.0754 0.5157 1.0000
4.750 0.9721 0.01846 0.00882 -0.0747 0.5086 1.0000
5.000 0.9957 0.01866 0.00904 -0.0738 0.5005 1.0000
5.250 1.0188 0.01883 0.00921 -0.0729 0.4907 1.0000
5.500 1.0408 0.01902 0.00945 -0.0718 0.4796 1.0000
5.750 1.0628 0.01918 0.00962 -0.0707 0.4677 1.0000
6.000 1.0845 0.01933 0.00979 -0.0695 0.4549 1.0000
6.250 1.1060 0.01951 0.01000 -0.0683 0.4424 1.0000
6.500 1.1271 0.01977 0.01037 -0.0672 0.4305 1.0000
6.750 1.1490 0.02005 0.01075 -0.0661 0.4211 1.0000
7.000 1.1707 0.02033 0.01112 -0.0651 0.4118 1.0000
7.250 1.1917 0.02065 0.01161 -0.0640 0.4008 1.0000
7.500 1.2115 0.02096 0.01202 -0.0627 0.3861 1.0000
7.750 1.2285 0.02128 0.01239 -0.0609 0.3590 1.0000
8.000 1.2424 0.02176 0.01277 -0.0587 0.3126 1.0000
8.750 1.2646 0.02498 0.01530 -0.0503 0.2124 1.0000
9.000 1.2730 0.02605 0.01635 -0.0478 0.1944 1.0000
9.250 1.2778 0.02724 0.01749 -0.0449 0.1721 1.0000
9.500 1.2787 0.02856 0.01875 -0.0416 0.1479 1.0000
9.750 1.2789 0.03004 0.02015 -0.0385 0.1314 1.0000
10.000 1.2811 0.03154 0.02164 -0.0361 0.1195 1.0000
10.250 1.2850 0.03305 0.02320 -0.0341 0.1102 1.0000
10.500 1.2875 0.03480 0.02498 -0.0323 0.1006 1.0000
10.750 1.2918 0.03653 0.02679 -0.0308 0.0855 1.0000
11.250 1.2867 0.04162 0.03175 -0.0284 0.0620 1.0000
11.500 1.2837 0.04442 0.03452 -0.0275 0.0557 1.0000
11.750 1.2876 0.04662 0.03689 -0.0268 0.0506 1.0000
12.000 1.2895 0.04906 0.03946 -0.0262 0.0458 1.0000
12.250 1.2944 0.05124 0.04181 -0.0257 0.0393 1.0000
12.500 1.2883 0.05465 0.04517 -0.0253 0.0244 1.0000
12.750 1.2817 0.05821 0.04869 -0.0250 0.0224 1.0000
13.000 1.2771 0.06165 0.05219 -0.0248 0.0211 1.0000
13.250 1.2727 0.06516 0.05583 -0.0248 0.0203 1.0000
13.500 1.2676 0.06887 0.05968 -0.0250 0.0196 1.0000
13.750 1.2621 0.07275 0.06373 -0.0254 0.0191 1.0000
14.000 1.2556 0.07687 0.06801 -0.0259 0.0187 1.0000
14.250 1.2490 0.08116 0.07247 -0.0267 0.0184 1.0000
14.500 1.2414 0.08572 0.07720 -0.0277 0.0182 1.0000
14.750 1.2330 0.09052 0.08216 -0.0289 0.0180 1.0000
15.000 1.2238 0.09559 0.08739 -0.0303 0.0178 1.0000
15.250 1.2141 0.10087 0.09287 -0.0319 0.0176 1.0000
15.500 1.2041 0.10633 0.09849 -0.0337 0.0175 1.0000
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Polar data table (+)
Polar graphs
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