Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Glenn Martin 4 (glennmartin4-il) Reynolds number: 50,000 Max Cl/Cd: 27.83 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-glennmartin4-il-50000-n5.txt Download as CSV file: xf-glennmartin4-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3486 0.12003 0.11449 -0.0223 1.0000 0.1085
-7.750 -0.3636 0.11789 0.11246 -0.0220 1.0000 0.1102
-7.500 -0.3792 0.11511 0.10974 -0.0302 0.9920 0.1122
-7.000 -0.3706 0.09992 0.09439 -0.0395 0.9774 0.0631
-6.750 -0.3632 0.09563 0.09007 -0.0422 0.9691 0.0626
-6.500 -0.3612 0.09085 0.08520 -0.0449 0.9589 0.0628
-6.250 -0.3548 0.08658 0.08087 -0.0463 0.9486 0.0622
-6.000 -0.3528 0.08151 0.07561 -0.0479 0.9370 0.0628
-5.750 -0.3439 0.07733 0.07130 -0.0486 0.9260 0.0622
-5.500 -0.3358 0.07284 0.06660 -0.0489 0.9149 0.0619
-5.250 -0.3244 0.06840 0.06189 -0.0492 0.9045 0.0617
-5.000 -0.3142 0.06412 0.05723 -0.0486 0.8932 0.0622
-4.750 -0.3082 0.06013 0.05272 -0.0465 0.8800 0.0634
-4.500 -0.2942 0.05757 0.05003 -0.0452 0.8679 0.0650
-4.250 -0.2728 0.05470 0.04687 -0.0449 0.8588 0.0670
-4.000 -0.2601 0.05202 0.04382 -0.0426 0.8460 0.0676
-3.750 -0.2460 0.04969 0.04107 -0.0403 0.8331 0.0702
-3.500 -0.2255 0.04693 0.03755 -0.0384 0.8239 0.0732
-3.250 -0.2053 0.04478 0.03509 -0.0368 0.8121 0.0752
-3.000 -0.1844 0.04308 0.03316 -0.0354 0.7995 0.0771
-2.750 -0.1530 0.04116 0.03082 -0.0353 0.7913 0.0826
-2.500 -0.1281 0.03952 0.02868 -0.0341 0.7790 0.0861
-2.250 -0.0998 0.03798 0.02700 -0.0338 0.7664 0.0894
-2.000 -0.0584 0.03623 0.02491 -0.0354 0.7586 0.0966
-1.750 -0.0222 0.03493 0.02350 -0.0365 0.7462 0.1040
-1.500 0.0235 0.03369 0.02196 -0.0393 0.7341 0.1131
-1.250 0.0792 0.03236 0.02054 -0.0442 0.7254 0.1309
-1.000 0.1227 0.03139 0.01946 -0.0469 0.7134 0.1522
-0.750 0.1584 0.03059 0.01862 -0.0483 0.7005 0.1811
-0.500 0.3853 0.02748 0.01787 -0.0874 0.6904 1.0000
-0.250 0.4207 0.02718 0.01708 -0.0885 0.6760 1.0000
0.000 0.4558 0.02696 0.01644 -0.0897 0.6623 1.0000
0.250 0.4863 0.02691 0.01603 -0.0901 0.6470 1.0000
0.500 0.5155 0.02696 0.01575 -0.0903 0.6326 1.0000
0.750 0.5442 0.02705 0.01554 -0.0906 0.6184 1.0000
1.000 0.5733 0.02719 0.01538 -0.0909 0.6050 1.0000
1.250 0.6052 0.02732 0.01522 -0.0918 0.5929 1.0000
1.500 0.6305 0.02759 0.01527 -0.0915 0.5798 1.0000
1.750 0.6530 0.02793 0.01543 -0.0907 0.5674 1.0000
2.000 0.6808 0.02821 0.01551 -0.0910 0.5566 1.0000
2.250 0.7067 0.02853 0.01564 -0.0909 0.5455 1.0000
2.500 0.7269 0.02896 0.01597 -0.0897 0.5346 1.0000
2.750 0.7580 0.02924 0.01604 -0.0906 0.5253 1.0000
3.000 0.7738 0.02975 0.01651 -0.0888 0.5152 1.0000
3.250 0.8009 0.03012 0.01673 -0.0889 0.5064 1.0000
3.500 0.8184 0.03064 0.01721 -0.0874 0.4977 1.0000
3.750 0.8446 0.03105 0.01750 -0.0875 0.4898 1.0000
4.000 0.8601 0.03166 0.01812 -0.0857 0.4822 1.0000
4.250 0.8907 0.03200 0.01831 -0.0866 0.4756 1.0000
4.500 0.8982 0.03275 0.01914 -0.0833 0.4680 1.0000
4.750 0.9209 0.03322 0.01953 -0.0828 0.4613 1.0000
5.000 0.9385 0.03384 0.02014 -0.0814 0.4555 1.0000
5.250 0.9500 0.03459 0.02095 -0.0790 0.4489 1.0000
5.500 0.9752 0.03507 0.02137 -0.0790 0.4440 1.0000
5.750 0.9871 0.03588 0.02223 -0.0768 0.4388 1.0000
6.000 0.9953 0.03679 0.02322 -0.0739 0.4332 1.0000
6.250 1.0167 0.03734 0.02374 -0.0732 0.4286 1.0000
6.500 1.0329 0.03809 0.02452 -0.0718 0.4240 1.0000
6.750 1.0309 0.03936 0.02593 -0.0675 0.4188 1.0000
7.000 1.0449 0.04018 0.02681 -0.0657 0.4142 1.0000
7.250 1.0724 0.04063 0.02723 -0.0662 0.4105 1.0000
7.500 1.0631 0.04227 0.02903 -0.0610 0.4060 1.0000
7.750 1.0566 0.04393 0.03083 -0.0565 0.4014 1.0000
8.000 1.0705 0.04479 0.03173 -0.0550 0.3972 1.0000
8.250 1.1031 0.04501 0.03193 -0.0561 0.3939 1.0000
8.500 1.0617 0.04837 0.03557 -0.0474 0.3892 1.0000
8.750 1.0367 0.05143 0.03880 -0.0418 0.3844 1.0000
9.000 1.0477 0.05259 0.04002 -0.0403 0.3808 1.0000
9.250 1.0876 0.05218 0.03959 -0.0418 0.3780 1.0000
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Polar data table (+)
Polar graphs
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