Glenn Martin 2 (glennmartin2-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Glenn Martin 2 (glennmartin2-il) Reynolds number: 100,000 Max Cl/Cd: 45.79 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-glennmartin2-il-100000-n5.txt Download as CSV file: xf-glennmartin2-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Glenn Martin 2
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1874 0.09686 0.09240 -0.0616 0.9650 0.0365
-9.250 -0.1871 0.09203 0.08760 -0.0656 0.9576 0.0368
-8.750 -0.1830 0.08328 0.07889 -0.0726 0.9421 0.0368
-8.500 -0.1776 0.07831 0.07389 -0.0774 0.9352 0.0368
-8.250 -0.1823 0.07312 0.06869 -0.0800 0.9231 0.0369
-8.000 -0.1736 0.06952 0.06506 -0.0819 0.9140 0.0375
-7.750 -0.1467 0.06835 0.06386 -0.0832 0.9071 0.0401
-7.500 -0.1417 0.06421 0.05964 -0.0850 0.8968 0.0411
-7.250 -0.1303 0.05825 0.05351 -0.0888 0.8894 0.0420
-7.000 -0.1311 0.05320 0.04828 -0.0887 0.8775 0.0423
-6.750 -0.1328 0.04511 0.03974 -0.0893 0.8684 0.0439
-6.500 -0.1334 0.03827 0.03217 -0.0879 0.8590 0.0461
-6.250 -0.1173 0.03700 0.03079 -0.0862 0.8488 0.0476
-6.000 -0.0918 0.03463 0.02809 -0.0864 0.8426 0.0499
-5.750 -0.0821 0.03226 0.02525 -0.0835 0.8311 0.0529
-5.500 -0.0563 0.02910 0.02130 -0.0832 0.8256 0.0555
-5.250 -0.0411 0.02824 0.02039 -0.0808 0.8138 0.0572
-5.000 -0.0162 0.02740 0.01941 -0.0801 0.8049 0.0604
-4.750 0.0108 0.02601 0.01764 -0.0796 0.7958 0.0638
-4.500 0.0316 0.02484 0.01608 -0.0778 0.7841 0.0660
-4.250 0.0591 0.02379 0.01493 -0.0775 0.7737 0.0692
-4.000 0.0900 0.02301 0.01401 -0.0778 0.7632 0.0739
-3.750 0.1147 0.02221 0.01297 -0.0767 0.7499 0.0779
-3.500 0.1421 0.02138 0.01195 -0.0762 0.7377 0.0819
-3.250 0.1712 0.02068 0.01122 -0.0762 0.7255 0.0881
-3.000 0.2033 0.02013 0.01042 -0.0766 0.7126 0.0964
-2.750 0.2348 0.01941 0.00969 -0.0771 0.6989 0.1046
-2.500 0.2673 0.01890 0.00904 -0.0778 0.6849 0.1150
-2.250 0.2982 0.01852 0.00855 -0.0781 0.6704 0.1276
-2.000 0.3287 0.01819 0.00819 -0.0784 0.6550 0.1419
-1.750 0.3588 0.01797 0.00797 -0.0787 0.6388 0.1597
-1.500 0.3875 0.01787 0.00785 -0.0786 0.6219 0.1827
-1.250 0.4133 0.01790 0.00781 -0.0780 0.6043 0.2172
-1.000 0.4352 0.01798 0.00781 -0.0767 0.5853 0.2465
-0.750 0.4556 0.01808 0.00777 -0.0751 0.5639 0.2683
-0.500 0.4762 0.01814 0.00771 -0.0736 0.5403 0.2858
-0.250 0.4958 0.01820 0.00766 -0.0719 0.5135 0.3022
0.000 0.5157 0.01826 0.00757 -0.0703 0.4887 0.3209
0.250 0.5352 0.01835 0.00750 -0.0688 0.4690 0.3415
0.500 0.5549 0.01843 0.00748 -0.0673 0.4540 0.3647
0.750 0.5742 0.01846 0.00752 -0.0658 0.4420 0.4014
1.250 0.7769 0.01896 0.00863 -0.0972 0.4132 1.0000
1.500 0.7968 0.01925 0.00880 -0.0958 0.4075 1.0000
1.750 0.8172 0.01957 0.00896 -0.0945 0.4029 1.0000
2.000 0.8386 0.01990 0.00914 -0.0934 0.3988 1.0000
2.250 0.8594 0.02019 0.00937 -0.0923 0.3945 1.0000
2.500 0.8807 0.02050 0.00960 -0.0912 0.3907 1.0000
2.750 0.9027 0.02084 0.00983 -0.0903 0.3870 1.0000
3.250 0.9470 0.02154 0.01038 -0.0886 0.3802 1.0000
3.500 0.9681 0.02188 0.01069 -0.0876 0.3766 1.0000
3.750 0.9901 0.02224 0.01102 -0.0867 0.3735 1.0000
4.000 1.0132 0.02262 0.01134 -0.0862 0.3707 1.0000
4.250 1.0379 0.02303 0.01167 -0.0859 0.3683 1.0000
4.500 1.0617 0.02345 0.01207 -0.0855 0.3660 1.0000
4.750 1.0822 0.02385 0.01253 -0.0844 0.3635 1.0000
5.000 1.1028 0.02426 0.01298 -0.0834 0.3608 1.0000
5.250 1.1239 0.02470 0.01345 -0.0825 0.3581 1.0000
5.500 1.1458 0.02513 0.01388 -0.0818 0.3553 1.0000
5.750 1.1694 0.02559 0.01432 -0.0814 0.3529 1.0000
6.000 1.1956 0.02611 0.01481 -0.0816 0.3507 1.0000
6.250 1.2119 0.02659 0.01540 -0.0799 0.3479 1.0000
6.500 1.2265 0.02706 0.01598 -0.0778 0.3445 1.0000
6.750 1.2421 0.02749 0.01648 -0.0760 0.3405 1.0000
7.000 1.2614 0.02792 0.01691 -0.0749 0.3367 1.0000
7.250 1.2856 0.02839 0.01733 -0.0747 0.3335 1.0000
7.500 1.2945 0.02893 0.01806 -0.0718 0.3303 1.0000
7.750 1.3068 0.02950 0.01875 -0.0695 0.3272 1.0000
8.000 1.3206 0.03002 0.01938 -0.0674 0.3241 1.0000
8.250 1.3375 0.03054 0.01997 -0.0660 0.3213 1.0000
8.500 1.3584 0.03100 0.02044 -0.0653 0.3184 1.0000
8.750 1.3613 0.03149 0.02106 -0.0614 0.3141 1.0000
9.000 1.3609 0.03201 0.02174 -0.0570 0.3093 1.0000
9.250 1.3676 0.03217 0.02185 -0.0538 0.3027 1.0000
9.500 1.3652 0.03273 0.02253 -0.0495 0.2967 1.0000
9.750 1.3658 0.03336 0.02332 -0.0459 0.2911 1.0000
10.000 1.3739 0.03375 0.02371 -0.0434 0.2858 1.0000
10.250 1.3732 0.03469 0.02484 -0.0401 0.2808 1.0000
10.500 1.3732 0.03559 0.02589 -0.0370 0.2748 1.0000
10.750 1.3758 0.03633 0.02666 -0.0344 0.2688 1.0000
11.000 1.3699 0.03776 0.02830 -0.0312 0.2609 1.0000
11.250 1.3719 0.03879 0.02938 -0.0290 0.2549 1.0000
11.500 1.3678 0.04057 0.03142 -0.0266 0.2468 1.0000
11.750 1.3660 0.04219 0.03313 -0.0246 0.2392 1.0000
12.000 1.3609 0.04430 0.03540 -0.0228 0.2299 1.0000
12.250 1.3560 0.04662 0.03786 -0.0213 0.2209 1.0000
12.500 1.3493 0.04924 0.04057 -0.0200 0.2113 1.0000
12.750 1.3384 0.05247 0.04386 -0.0189 0.1993 1.0000
13.000 1.3235 0.05638 0.04779 -0.0182 0.1876 1.0000
13.250 1.3051 0.06102 0.05247 -0.0179 0.1779 1.0000
13.500 1.2834 0.06639 0.05791 -0.0180 0.1712 1.0000
13.750 1.2636 0.07192 0.06360 -0.0185 0.1683 1.0000
14.000 1.2377 0.07857 0.07039 -0.0195 0.1640 1.0000
14.250 1.2165 0.08486 0.07683 -0.0207 0.1620 1.0000
14.500 1.1970 0.09099 0.08306 -0.0220 0.1581 1.0000
14.750 1.1794 0.09698 0.08919 -0.0233 0.1544 1.0000
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Polar data table (+)
Polar graphs
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