GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il) Reynolds number: 100,000 Max Cl/Cd: 54.31 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe140-il-100000.txt Download as CSV file: xf-goe140-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 140 (MVA H.17) 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2156 0.10213 0.09770 -0.0256 1.0000 0.0560
-8.750 -0.2115 0.09906 0.09467 -0.0260 1.0000 0.0574
-8.500 -0.3028 0.10740 0.10273 -0.0205 1.0000 0.0540
-8.250 -0.2944 0.10390 0.09925 -0.0206 1.0000 0.0554
-8.000 -0.2883 0.10095 0.09635 -0.0212 1.0000 0.0568
-7.750 -0.2839 0.09826 0.09371 -0.0220 1.0000 0.0583
-7.500 -0.2817 0.09584 0.09136 -0.0226 1.0000 0.0598
-7.250 -0.2816 0.09377 0.08937 -0.0235 1.0000 0.0615
-7.000 -0.2812 0.09261 0.08831 -0.0277 1.0000 0.0631
-6.750 -0.2783 0.09237 0.08812 -0.0355 1.0000 0.0638
-6.500 -0.2750 0.09031 0.08609 -0.0389 1.0000 0.0642
-6.250 -0.2785 0.08490 0.08083 -0.0310 1.0000 0.0651
-6.000 -0.2812 0.08221 0.07823 -0.0274 1.0000 0.0661
-5.750 -0.2850 0.08023 0.07632 -0.0253 1.0000 0.0671
-5.500 -0.2884 0.07844 0.07459 -0.0241 1.0000 0.0682
-5.250 -0.2900 0.07665 0.07284 -0.0237 1.0000 0.0696
-5.000 -0.1992 0.07322 0.06881 -0.0502 0.9886 0.0765
-4.750 -0.1814 0.06585 0.06169 -0.0498 0.9831 0.0783
-4.500 -0.1458 0.06154 0.05735 -0.0544 0.9736 0.0830
-4.250 -0.0778 0.05720 0.05257 -0.0691 0.9634 0.0905
-4.000 -0.0417 0.05237 0.04779 -0.0729 0.9564 0.0943
-3.750 0.0176 0.04888 0.04389 -0.0829 0.9454 0.1048
-3.500 0.0568 0.04493 0.03997 -0.0870 0.9364 0.1136
-3.250 0.1051 0.04131 0.03613 -0.0931 0.9266 0.1238
-3.000 0.1477 0.03842 0.03301 -0.0975 0.9128 0.1366
-2.750 0.1853 0.03581 0.03023 -0.1003 0.8979 0.1518
-2.500 0.2212 0.03379 0.02793 -0.1026 0.8816 0.1773
-2.250 0.2471 0.03165 0.02572 -0.1029 0.8621 0.2079
-1.250 0.3406 0.02496 0.01879 -0.0993 0.7793 0.3709
-1.000 0.3740 0.02381 0.01724 -0.1000 0.7586 0.3727
-0.750 0.4159 0.02283 0.01560 -0.1017 0.7361 0.3018
-0.500 0.4641 0.02299 0.01440 -0.1008 0.7168 0.1480
-0.250 0.4938 0.02251 0.01348 -0.0997 0.6961 0.1323
0.000 0.5216 0.02127 0.01207 -0.0992 0.6759 0.1240
0.250 0.5503 0.02089 0.01129 -0.0982 0.6572 0.1163
0.500 0.5779 0.02025 0.01043 -0.0976 0.6397 0.1140
0.750 0.6053 0.01980 0.00982 -0.0970 0.6216 0.1135
1.000 0.6326 0.01947 0.00933 -0.0964 0.6049 0.1153
1.250 0.6590 0.01910 0.00892 -0.0958 0.5893 0.1233
1.500 0.6855 0.01891 0.00863 -0.0952 0.5748 0.1318
1.750 0.7126 0.01867 0.00828 -0.0947 0.5616 0.1451
2.250 0.7633 0.01682 0.00790 -0.0930 0.5372 1.0000
2.500 0.7905 0.01721 0.00803 -0.0927 0.5252 1.0000
2.750 0.8176 0.01762 0.00823 -0.0925 0.5144 1.0000
3.000 0.8449 0.01803 0.00842 -0.0923 0.5047 1.0000
3.250 0.8716 0.01848 0.00882 -0.0922 0.4944 1.0000
3.500 0.8987 0.01896 0.00919 -0.0921 0.4861 1.0000
3.750 0.9256 0.01944 0.00961 -0.0920 0.4775 1.0000
4.000 0.9524 0.01999 0.01011 -0.0919 0.4699 1.0000
4.250 0.9792 0.02049 0.01060 -0.0918 0.4624 1.0000
4.500 1.0058 0.02108 0.01117 -0.0917 0.4556 1.0000
4.750 1.0322 0.02164 0.01175 -0.0916 0.4486 1.0000
5.000 1.0594 0.02224 0.01227 -0.0916 0.4434 1.0000
5.250 1.0846 0.02296 0.01319 -0.0914 0.4371 1.0000
5.500 1.1112 0.02358 0.01382 -0.0914 0.4321 1.0000
5.750 1.1372 0.02430 0.01458 -0.0913 0.4272 1.0000
6.000 1.1618 0.02504 0.01552 -0.0911 0.4211 1.0000
6.250 1.1884 0.02557 0.01605 -0.0909 0.4159 1.0000
6.500 1.2119 0.02617 0.01680 -0.0905 0.4080 1.0000
6.750 1.2386 0.02618 0.01666 -0.0900 0.3984 1.0000
7.000 1.2621 0.02616 0.01673 -0.0892 0.3864 1.0000
7.250 1.2850 0.02623 0.01689 -0.0884 0.3747 1.0000
7.500 1.3107 0.02651 0.01716 -0.0880 0.3679 1.0000
7.750 1.3332 0.02673 0.01754 -0.0873 0.3583 1.0000
8.000 1.3554 0.02663 0.01755 -0.0863 0.3458 1.0000
8.250 1.3772 0.02651 0.01748 -0.0852 0.3332 1.0000
8.500 1.4003 0.02655 0.01754 -0.0844 0.3236 1.0000
8.750 1.4210 0.02672 0.01791 -0.0833 0.3130 1.0000
9.000 1.4396 0.02670 0.01804 -0.0818 0.2984 1.0000
9.250 1.4576 0.02684 0.01837 -0.0803 0.2837 1.0000
9.500 1.4762 0.02718 0.01893 -0.0790 0.2707 1.0000
9.750 1.4919 0.02753 0.01940 -0.0772 0.2516 1.0000
10.000 1.5039 0.02819 0.02016 -0.0751 0.2151 1.0000
10.250 1.4958 0.03053 0.02182 -0.0714 0.1253 1.0000
10.500 1.4833 0.03347 0.02454 -0.0672 0.0943 1.0000
10.750 1.4717 0.03623 0.02723 -0.0634 0.0653 1.0000
11.000 1.4593 0.03935 0.03033 -0.0607 0.0544 1.0000
11.250 1.4472 0.04286 0.03394 -0.0590 0.0493 1.0000
11.500 1.4357 0.04676 0.03799 -0.0583 0.0466 1.0000
11.750 1.4235 0.05118 0.04261 -0.0584 0.0448 1.0000
12.000 1.4091 0.05631 0.04794 -0.0593 0.0437 1.0000
12.250 1.3927 0.06210 0.05393 -0.0608 0.0430 1.0000
12.500 1.3751 0.06834 0.06036 -0.0626 0.0426 1.0000
12.750 1.3573 0.07474 0.06693 -0.0645 0.0422 1.0000
13.000 1.3405 0.08101 0.07336 -0.0663 0.0419 1.0000
13.250 1.3250 0.08704 0.07953 -0.0680 0.0415 1.0000
13.500 1.3113 0.09278 0.08538 -0.0695 0.0410 1.0000
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Polar data table (+)
Polar graphs
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