Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Glenn Martin 4 (glennmartin4-il) Reynolds number: 100,000 Max Cl/Cd: 40.85 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-glennmartin4-il-100000-n5.txt Download as CSV file: xf-glennmartin4-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2547 0.09723 0.09290 -0.0571 0.9613 0.0356
-7.750 -0.2590 0.09273 0.08844 -0.0599 0.9540 0.0350
-7.500 -0.2695 0.08817 0.08390 -0.0624 0.9455 0.0342
-7.250 -0.2833 0.08376 0.07947 -0.0631 0.9359 0.0340
-7.000 -0.2887 0.07907 0.07473 -0.0644 0.9268 0.0348
-6.500 -0.2926 0.06872 0.06413 -0.0659 0.9086 0.0350
-6.250 -0.2948 0.06407 0.05932 -0.0647 0.8979 0.0351
-6.000 -0.2920 0.05837 0.05330 -0.0640 0.8897 0.0362
-5.750 -0.2898 0.05397 0.04861 -0.0617 0.8795 0.0362
-5.500 -0.2901 0.04921 0.04345 -0.0582 0.8688 0.0366
-5.250 -0.2874 0.04338 0.03686 -0.0546 0.8615 0.0384
-5.000 -0.2763 0.04178 0.03513 -0.0519 0.8502 0.0393
-4.750 -0.2516 0.04009 0.03326 -0.0516 0.8442 0.0410
-4.500 -0.2424 0.03775 0.03056 -0.0479 0.8321 0.0419
-4.250 -0.2203 0.03496 0.02723 -0.0463 0.8265 0.0443
-4.000 -0.2080 0.03266 0.02434 -0.0426 0.8138 0.0464
-3.750 -0.1846 0.03157 0.02317 -0.0415 0.8022 0.0481
-3.500 -0.1541 0.02994 0.02125 -0.0413 0.7932 0.0502
-3.250 -0.1306 0.02861 0.01955 -0.0398 0.7786 0.0535
-3.000 -0.1033 0.02743 0.01815 -0.0392 0.7639 0.0559
-2.750 -0.0730 0.02637 0.01693 -0.0392 0.7492 0.0587
-2.500 -0.0400 0.02536 0.01563 -0.0396 0.7361 0.0628
-2.250 -0.0046 0.02439 0.01455 -0.0408 0.7215 0.0670
-2.000 0.0338 0.02337 0.01330 -0.0424 0.7061 0.0719
-1.750 0.0721 0.02243 0.01227 -0.0442 0.6901 0.0791
-1.500 0.1095 0.02157 0.01127 -0.0459 0.6732 0.0887
-1.250 0.1447 0.02094 0.01050 -0.0471 0.6573 0.0989
-1.000 0.1793 0.02051 0.00994 -0.0484 0.6420 0.1112
-0.750 0.2141 0.02023 0.00954 -0.0498 0.6269 0.1274
-0.500 0.2485 0.02000 0.00925 -0.0513 0.6128 0.1485
0.000 0.5771 0.01940 0.01037 -0.1107 0.5648 1.0000
0.250 0.5994 0.01953 0.01029 -0.1098 0.5530 1.0000
0.500 0.6229 0.01969 0.01021 -0.1091 0.5420 1.0000
0.750 0.6426 0.01985 0.01021 -0.1077 0.5307 1.0000
1.000 0.6628 0.02003 0.01023 -0.1064 0.5197 1.0000
1.250 0.6839 0.02022 0.01023 -0.1053 0.5098 1.0000
1.500 0.7020 0.02042 0.01033 -0.1036 0.4992 1.0000
1.750 0.7225 0.02064 0.01039 -0.1024 0.4900 1.0000
2.000 0.7415 0.02085 0.01051 -0.1009 0.4809 1.0000
2.250 0.7612 0.02108 0.01062 -0.0995 0.4723 1.0000
2.500 0.7793 0.02132 0.01077 -0.0978 0.4631 1.0000
2.750 0.7987 0.02157 0.01092 -0.0964 0.4553 1.0000
3.000 0.8167 0.02183 0.01110 -0.0948 0.4468 1.0000
3.250 0.8356 0.02211 0.01127 -0.0933 0.4392 1.0000
3.500 0.8536 0.02238 0.01150 -0.0917 0.4315 1.0000
3.750 0.8730 0.02268 0.01168 -0.0904 0.4250 1.0000
4.000 0.8923 0.02298 0.01198 -0.0891 0.4186 1.0000
4.250 0.9113 0.02329 0.01222 -0.0877 0.4127 1.0000
4.500 0.9311 0.02362 0.01248 -0.0866 0.4074 1.0000
4.750 0.9497 0.02396 0.01281 -0.0852 0.4014 1.0000
5.000 0.9683 0.02429 0.01309 -0.0838 0.3962 1.0000
5.250 0.9886 0.02466 0.01341 -0.0828 0.3916 1.0000
5.500 1.0067 0.02503 0.01381 -0.0814 0.3865 1.0000
5.750 1.0256 0.02541 0.01418 -0.0802 0.3821 1.0000
6.000 1.0472 0.02579 0.01449 -0.0795 0.3786 1.0000
6.250 1.0662 0.02621 0.01493 -0.0784 0.3747 1.0000
6.500 1.0835 0.02665 0.01544 -0.0769 0.3700 1.0000
6.750 1.1023 0.02708 0.01588 -0.0757 0.3663 1.0000
7.000 1.1231 0.02749 0.01625 -0.0750 0.3627 1.0000
7.250 1.1426 0.02797 0.01676 -0.0741 0.3594 1.0000
7.500 1.1592 0.02849 0.01737 -0.0726 0.3559 1.0000
7.750 1.1755 0.02899 0.01796 -0.0711 0.3521 1.0000
8.000 1.1942 0.02947 0.01845 -0.0701 0.3488 1.0000
8.250 1.2171 0.02994 0.01892 -0.0698 0.3459 1.0000
8.500 1.2320 0.03053 0.01962 -0.0682 0.3428 1.0000
8.750 1.2435 0.03118 0.02041 -0.0660 0.3391 1.0000
9.000 1.2576 0.03178 0.02110 -0.0642 0.3358 1.0000
9.250 1.2752 0.03234 0.02172 -0.0631 0.3326 1.0000
9.500 1.2963 0.03284 0.02224 -0.0627 0.3298 1.0000
9.750 1.3085 0.03356 0.02308 -0.0608 0.3267 1.0000
10.000 1.3152 0.03442 0.02413 -0.0580 0.3235 1.0000
10.250 1.3249 0.03521 0.02506 -0.0558 0.3202 1.0000
10.500 1.3381 0.03590 0.02586 -0.0541 0.3170 1.0000
10.750 1.3573 0.03646 0.02647 -0.0535 0.3141 1.0000
11.000 1.3666 0.03726 0.02737 -0.0513 0.3107 1.0000
11.250 1.3602 0.03851 0.02886 -0.0469 0.3066 1.0000
11.500 1.3600 0.03935 0.02979 -0.0435 0.3007 1.0000
11.750 1.3709 0.03983 0.03025 -0.0417 0.2953 1.0000
12.000 1.3577 0.04158 0.03226 -0.0370 0.2906 1.0000
12.250 1.3533 0.04286 0.03366 -0.0337 0.2848 1.0000
12.500 1.3571 0.04374 0.03457 -0.0314 0.2790 1.0000
12.750 1.3429 0.04606 0.03715 -0.0277 0.2743 1.0000
13.000 1.3362 0.04795 0.03918 -0.0250 0.2688 1.0000
13.250 1.3355 0.04945 0.04074 -0.0230 0.2633 1.0000
13.500 1.3144 0.05293 0.04447 -0.0201 0.2573 1.0000
13.750 1.3049 0.05547 0.04708 -0.0182 0.2500 1.0000
14.000 1.2854 0.05948 0.05130 -0.0166 0.2445 1.0000
14.250 1.2664 0.06379 0.05580 -0.0156 0.2393 1.0000
14.500 1.2529 0.06757 0.05965 -0.0150 0.2327 1.0000
14.750 1.2194 0.07431 0.06664 -0.0148 0.2290 1.0000
15.000 1.1810 0.08211 0.07464 -0.0152 0.2266 1.0000
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Polar data table (+)
Polar graphs
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