Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Glenn Martin 4 (glennmartin4-il) Reynolds number: 200,000 Max Cl/Cd: 49.71 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-glennmartin4-il-200000-n5.txt Download as CSV file: xf-glennmartin4-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Glenn Martin 4
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2160 0.09486 0.09151 -0.0698 0.9544 0.0192
-8.750 -0.2129 0.08959 0.08625 -0.0743 0.9515 0.0192
-8.500 -0.2193 0.08535 0.08205 -0.0756 0.9442 0.0189
-8.250 -0.2638 0.07510 0.07181 -0.0817 0.9336 0.0198
-7.750 -0.2865 0.06610 0.06270 -0.0818 0.9189 0.0194
-7.250 -0.3206 0.05399 0.05024 -0.0774 0.8983 0.0203
-7.000 -0.3071 0.05143 0.04754 -0.0771 0.8936 0.0209
-6.750 -0.3178 0.04635 0.04218 -0.0729 0.8835 0.0212
-6.500 -0.3294 0.03834 0.03352 -0.0682 0.8776 0.0220
-6.250 -0.3410 0.03364 0.02820 -0.0616 0.8673 0.0228
-6.000 -0.3339 0.02964 0.02331 -0.0577 0.8619 0.0250
-5.750 -0.3218 0.02828 0.02178 -0.0547 0.8532 0.0254
-5.500 -0.2999 0.02757 0.02105 -0.0535 0.8470 0.0267
-5.250 -0.2783 0.02630 0.01954 -0.0521 0.8403 0.0282
-5.000 -0.2596 0.02492 0.01785 -0.0499 0.8305 0.0293
-4.750 -0.2343 0.02367 0.01625 -0.0489 0.8200 0.0312
-4.500 -0.2018 0.02223 0.01468 -0.0496 0.8100 0.0327
-4.250 -0.1715 0.02133 0.01364 -0.0497 0.7962 0.0344
-4.000 -0.1346 0.02025 0.01233 -0.0512 0.7809 0.0366
-3.750 -0.0966 0.01927 0.01112 -0.0529 0.7668 0.0387
-3.500 -0.0549 0.01839 0.01016 -0.0556 0.7488 0.0409
-3.250 -0.0105 0.01770 0.00929 -0.0588 0.7249 0.0441
-3.000 0.0320 0.01704 0.00837 -0.0617 0.6946 0.0463
-2.750 0.0649 0.01678 0.00794 -0.0627 0.6645 0.0493
-2.500 0.0912 0.01662 0.00760 -0.0623 0.6423 0.0524
-2.250 0.1148 0.01652 0.00735 -0.0613 0.6232 0.0562
-2.000 0.1372 0.01645 0.00714 -0.0601 0.6075 0.0607
-1.750 0.1588 0.01639 0.00694 -0.0588 0.5925 0.0665
-1.500 0.1806 0.01637 0.00678 -0.0575 0.5799 0.0746
-1.250 0.2012 0.01625 0.00659 -0.0561 0.5680 0.0813
-1.000 0.2226 0.01620 0.00643 -0.0549 0.5576 0.0873
-0.750 0.2436 0.01613 0.00631 -0.0536 0.5473 0.0933
-0.500 0.2651 0.01613 0.00622 -0.0523 0.5374 0.0981
-0.250 0.2869 0.01612 0.00617 -0.0512 0.5286 0.1055
0.000 0.3082 0.01611 0.00616 -0.0500 0.5188 0.1164
0.250 0.3295 0.01616 0.00616 -0.0488 0.5093 0.1298
0.500 0.3516 0.01611 0.00617 -0.0478 0.4999 0.1599
0.750 0.3744 0.01589 0.00619 -0.0472 0.4911 0.2439
1.250 0.6831 0.01644 0.00833 -0.1049 0.4512 1.0000
1.500 0.7000 0.01661 0.00838 -0.1029 0.4419 1.0000
1.750 0.7177 0.01677 0.00845 -0.1010 0.4315 1.0000
2.000 0.7352 0.01696 0.00853 -0.0992 0.4232 1.0000
2.250 0.7527 0.01715 0.00863 -0.0974 0.4139 1.0000
2.500 0.7707 0.01735 0.00875 -0.0956 0.4059 1.0000
2.750 0.7890 0.01756 0.00888 -0.0940 0.3985 1.0000
3.000 0.8070 0.01779 0.00902 -0.0923 0.3919 1.0000
3.250 0.8259 0.01801 0.00918 -0.0908 0.3849 1.0000
3.500 0.8439 0.01826 0.00936 -0.0892 0.3793 1.0000
3.750 0.8627 0.01851 0.00955 -0.0878 0.3733 1.0000
4.000 0.8820 0.01875 0.00975 -0.0864 0.3684 1.0000
4.250 0.8997 0.01904 0.00997 -0.0848 0.3632 1.0000
4.500 0.9186 0.01931 0.01020 -0.0834 0.3585 1.0000
4.750 0.9381 0.01957 0.01044 -0.0822 0.3542 1.0000
5.000 0.9572 0.01985 0.01069 -0.0809 0.3504 1.0000
5.250 0.9758 0.02017 0.01097 -0.0796 0.3468 1.0000
5.500 0.9953 0.02047 0.01124 -0.0784 0.3437 1.0000
5.750 1.0149 0.02074 0.01154 -0.0773 0.3400 1.0000
6.000 1.0343 0.02104 0.01184 -0.0762 0.3367 1.0000
6.250 1.0527 0.02136 0.01215 -0.0749 0.3333 1.0000
6.500 1.0714 0.02173 0.01250 -0.0737 0.3304 1.0000
6.750 1.0910 0.02207 0.01283 -0.0727 0.3280 1.0000
7.000 1.1102 0.02239 0.01320 -0.0716 0.3250 1.0000
7.250 1.1286 0.02272 0.01359 -0.0704 0.3218 1.0000
7.500 1.1472 0.02308 0.01397 -0.0692 0.3191 1.0000
7.750 1.1652 0.02346 0.01438 -0.0680 0.3164 1.0000
8.000 1.1836 0.02387 0.01477 -0.0669 0.3138 1.0000
8.250 1.2016 0.02429 0.01522 -0.0658 0.3109 1.0000
8.500 1.2192 0.02467 0.01570 -0.0646 0.3086 1.0000
8.750 1.2366 0.02508 0.01619 -0.0633 0.3060 1.0000
9.000 1.2533 0.02550 0.01668 -0.0620 0.3035 1.0000
9.250 1.2686 0.02597 0.01720 -0.0605 0.3003 1.0000
9.500 1.2854 0.02645 0.01770 -0.0593 0.2979 1.0000
9.750 1.3003 0.02696 0.01826 -0.0578 0.2946 1.0000
10.000 1.3078 0.02756 0.01900 -0.0551 0.2888 1.0000
10.250 1.3176 0.02818 0.01967 -0.0528 0.2840 1.0000
10.500 1.3272 0.02886 0.02036 -0.0506 0.2793 1.0000
10.750 1.3369 0.02954 0.02121 -0.0485 0.2743 1.0000
11.000 1.3462 0.03027 0.02202 -0.0465 0.2695 1.0000
11.250 1.3520 0.03117 0.02293 -0.0440 0.2638 1.0000
11.500 1.3615 0.03197 0.02389 -0.0422 0.2583 1.0000
11.750 1.3679 0.03295 0.02495 -0.0400 0.2521 1.0000
12.000 1.3715 0.03413 0.02621 -0.0377 0.2426 1.0000
12.250 1.3726 0.03553 0.02764 -0.0352 0.2342 1.0000
12.500 1.3728 0.03711 0.02928 -0.0329 0.2201 1.0000
12.750 1.3673 0.03920 0.03135 -0.0303 0.2011 1.0000
13.000 1.3547 0.04198 0.03405 -0.0274 0.1796 1.0000
13.250 1.3425 0.04495 0.03699 -0.0249 0.1633 1.0000
13.500 1.3219 0.04892 0.04089 -0.0225 0.1423 1.0000
13.750 1.3016 0.05317 0.04512 -0.0206 0.1256 1.0000
14.250 1.2538 0.06325 0.05519 -0.0184 0.0769 1.0000
14.500 1.2304 0.06862 0.06059 -0.0180 0.0622 1.0000
14.750 1.1984 0.07527 0.06726 -0.0178 0.0500 1.0000
15.000 1.1776 0.08074 0.07284 -0.0180 0.0430 1.0000
15.250 1.1609 0.08583 0.07805 -0.0183 0.0372 1.0000
15.500 1.1457 0.09079 0.08312 -0.0189 0.0331 1.0000
15.750 1.1299 0.09598 0.08841 -0.0195 0.0292 1.0000
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Polar data table (+)
Polar graphs
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