Glenn Martin 2 (glennmartin2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Glenn Martin 2 (glennmartin2-il) Reynolds number: 100,000 Max Cl/Cd: 46.23 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin2-il-100000.txt Download as CSV file: xf-glennmartin2-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3268 0.11958 0.11567 -0.0214 1.0000 0.0887
-9.000 -0.3537 0.11968 0.11588 -0.0210 1.0000 0.0892
-8.750 -0.3788 0.11932 0.11563 -0.0201 0.9997 0.0894
-8.500 -0.3534 0.11214 0.10845 -0.0245 0.9942 0.0908
-8.250 -0.3062 0.10621 0.10246 -0.0252 0.9894 0.0946
-8.000 -0.2850 0.10213 0.09835 -0.0309 0.9815 0.0986
-7.750 -0.2853 0.09911 0.09533 -0.0382 0.9697 0.1029
-7.500 -0.2952 0.09672 0.09278 -0.0521 0.9491 0.1050
-7.250 -0.2576 0.09028 0.08648 -0.0465 0.9486 0.1090
-7.000 -0.2364 0.08654 0.08270 -0.0501 0.9393 0.1155
-6.750 -0.2370 0.08270 0.07865 -0.0598 0.9222 0.1213
-6.500 -0.2091 0.07822 0.07426 -0.0585 0.9175 0.1243
-6.250 -0.1903 0.07512 0.07111 -0.0600 0.9081 0.1309
-6.000 -0.1699 0.07090 0.06676 -0.0644 0.8998 0.1395
-5.500 -0.1248 0.06443 0.06013 -0.0677 0.8832 0.1591
-5.250 -0.1154 0.06176 0.05731 -0.0680 0.8705 0.1693
-5.000 -0.0983 0.05952 0.05487 -0.0686 0.8603 0.1833
-4.750 -0.0710 0.05670 0.05192 -0.0699 0.8538 0.1989
-4.500 -0.0541 0.05386 0.04915 -0.0681 0.8452 0.2055
-4.250 -0.0346 0.04211 0.03603 -0.0707 0.8381 0.1169
-4.000 -0.0195 0.03894 0.03247 -0.0686 0.8290 0.1143
-3.750 0.0078 0.03460 0.02740 -0.0679 0.8231 0.1104
-3.500 0.0516 0.03171 0.02401 -0.0697 0.8200 0.1149
-3.250 0.0678 0.03034 0.02223 -0.0670 0.8084 0.1180
-3.000 0.1183 0.02767 0.01916 -0.0699 0.8052 0.1242
-2.750 0.1420 0.02676 0.01813 -0.0684 0.7938 0.1332
-2.500 0.1991 0.02470 0.01594 -0.0726 0.7897 0.1476
-2.250 0.2271 0.02385 0.01509 -0.0718 0.7779 0.1615
-2.000 0.2804 0.02257 0.01376 -0.0755 0.7708 0.1843
-1.750 0.3166 0.02185 0.01307 -0.0761 0.7587 0.2055
-1.500 0.3504 0.02115 0.01227 -0.0762 0.7442 0.2299
-1.250 0.3886 0.02025 0.01137 -0.0773 0.7280 0.2629
-1.000 0.4280 0.01908 0.01030 -0.0787 0.7082 0.3237
-0.750 0.4758 0.01799 0.00931 -0.0820 0.6819 0.3836
-0.500 0.7057 0.01668 0.00877 -0.1220 0.6140 1.0000
-0.250 0.7248 0.01706 0.00882 -0.1201 0.5862 1.0000
0.000 0.7457 0.01740 0.00883 -0.1186 0.5651 1.0000
0.250 0.7637 0.01770 0.00893 -0.1166 0.5465 1.0000
0.500 0.7832 0.01799 0.00898 -0.1150 0.5320 1.0000
0.750 0.8030 0.01826 0.00906 -0.1134 0.5196 1.0000
1.000 0.8226 0.01857 0.00922 -0.1119 0.5086 1.0000
1.250 0.8447 0.01889 0.00934 -0.1109 0.5002 1.0000
1.500 0.8659 0.01923 0.00956 -0.1097 0.4920 1.0000
1.750 0.8896 0.01959 0.00975 -0.1091 0.4856 1.0000
2.000 0.9106 0.01999 0.01008 -0.1079 0.4790 1.0000
2.250 0.9355 0.02038 0.01031 -0.1076 0.4735 1.0000
2.500 0.9569 0.02084 0.01071 -0.1066 0.4681 1.0000
2.750 0.9783 0.02128 0.01110 -0.1055 0.4625 1.0000
3.000 1.0045 0.02173 0.01141 -0.1055 0.4579 1.0000
3.250 1.0263 0.02227 0.01193 -0.1046 0.4537 1.0000
3.500 1.0459 0.02281 0.01251 -0.1033 0.4496 1.0000
3.750 1.0685 0.02336 0.01302 -0.1027 0.4458 1.0000
4.000 1.0949 0.02392 0.01351 -0.1027 0.4423 1.0000
4.250 1.1167 0.02457 0.01416 -0.1020 0.4388 1.0000
4.500 1.1321 0.02522 0.01491 -0.1000 0.4349 1.0000
4.750 1.1516 0.02587 0.01562 -0.0988 0.4313 1.0000
5.000 1.1743 0.02653 0.01628 -0.0982 0.4282 1.0000
5.250 1.2035 0.02727 0.01691 -0.0989 0.4248 1.0000
5.500 1.2116 0.02803 0.01787 -0.0956 0.4207 1.0000
5.750 1.2263 0.02870 0.01863 -0.0936 0.4157 1.0000
6.000 1.2502 0.02930 0.01920 -0.0933 0.4111 1.0000
6.250 1.2707 0.03013 0.02004 -0.0924 0.4071 1.0000
6.500 1.2773 0.03102 0.02113 -0.0890 0.4031 1.0000
6.750 1.2922 0.03183 0.02205 -0.0872 0.3991 1.0000
7.000 1.3157 0.03254 0.02275 -0.0869 0.3950 1.0000
7.250 1.3372 0.03350 0.02373 -0.0863 0.3914 1.0000
7.500 1.3353 0.03463 0.02512 -0.0817 0.3875 1.0000
7.750 1.3439 0.03565 0.02630 -0.0789 0.3835 1.0000
8.000 1.3668 0.03638 0.02704 -0.0785 0.3793 1.0000
8.250 1.3920 0.03734 0.02800 -0.0787 0.3752 1.0000
8.500 1.3768 0.03879 0.02975 -0.0721 0.3709 1.0000
8.750 1.3929 0.03927 0.03027 -0.0704 0.3646 1.0000
9.000 1.4143 0.03947 0.03044 -0.0696 0.3569 1.0000
9.250 1.4169 0.03987 0.03094 -0.0657 0.3494 1.0000
9.500 1.4440 0.03962 0.03059 -0.0657 0.3410 1.0000
9.750 1.4341 0.04068 0.03185 -0.0600 0.3357 1.0000
10.000 1.4867 0.03967 0.03060 -0.0640 0.3272 1.0000
10.250 1.4587 0.04120 0.03245 -0.0556 0.3233 1.0000
10.500 1.4553 0.04164 0.03297 -0.0509 0.3173 1.0000
10.750 1.4841 0.04084 0.03205 -0.0509 0.3094 1.0000
11.000 1.4595 0.04221 0.03365 -0.0436 0.3049 1.0000
11.250 1.5031 0.04044 0.03166 -0.0455 0.2961 1.0000
11.500 1.4748 0.04229 0.03381 -0.0383 0.2924 1.0000
11.750 1.4582 0.04377 0.03549 -0.0334 0.2874 1.0000
12.000 1.4922 0.04220 0.03374 -0.0337 0.2799 1.0000
12.250 1.4618 0.04493 0.03679 -0.0280 0.2762 1.0000
12.500 1.4480 0.04658 0.03860 -0.0243 0.2706 1.0000
12.750 1.4639 0.04604 0.03801 -0.0231 0.2639 1.0000
13.000 1.4331 0.04972 0.04198 -0.0193 0.2596 1.0000
13.250 1.4306 0.05092 0.04326 -0.0174 0.2532 1.0000
13.500 1.4201 0.05330 0.04577 -0.0156 0.2480 1.0000
13.750 1.3843 0.05889 0.05161 -0.0138 0.2442 1.0000
14.000 1.4008 0.05849 0.05118 -0.0132 0.2361 1.0000
14.250 1.3483 0.06706 0.06005 -0.0128 0.2335 1.0000
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Polar data table (+)
Polar graphs
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