Glenn Martin 3 (glennmartin3-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: Glenn Martin 3 (glennmartin3-il) Reynolds number: 200,000 Max Cl/Cd: 47.06 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-glennmartin3-il-200000-n5.txt Download as CSV file: xf-glennmartin3-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Glenn Martin 3
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2985 0.10347 0.09982 -0.0573 0.9750 0.0227
-10.250 -0.3043 0.09747 0.09385 -0.0611 0.9716 0.0238
-10.000 -0.3089 0.09082 0.08721 -0.0661 0.9692 0.0236
-9.750 -0.2931 0.09104 0.08745 -0.0652 0.9658 0.0249
-9.250 -0.3159 0.07840 0.07485 -0.0749 0.9566 0.0245
-9.000 -0.3680 0.06676 0.06308 -0.0803 0.9481 0.0239
-8.750 -0.3844 0.06456 0.06084 -0.0763 0.9396 0.0242
-8.500 -0.4183 0.05752 0.05357 -0.0727 0.9308 0.0241
-8.250 -0.4283 0.05252 0.04834 -0.0701 0.9257 0.0246
-8.000 -0.4478 0.04800 0.04353 -0.0644 0.9178 0.0248
-7.750 -0.4534 0.04415 0.03932 -0.0602 0.9130 0.0260
-7.500 -0.4686 0.03955 0.03418 -0.0537 0.9071 0.0266
-7.250 -0.4872 0.03510 0.02886 -0.0454 0.8997 0.0279
-7.000 -0.4667 0.03378 0.02744 -0.0442 0.8972 0.0285
-6.750 -0.4420 0.03273 0.02628 -0.0437 0.8954 0.0292
-6.500 -0.4451 0.03165 0.02500 -0.0376 0.8864 0.0295
-6.250 -0.4254 0.03038 0.02349 -0.0358 0.8832 0.0305
-6.000 -0.4021 0.02874 0.02145 -0.0345 0.8809 0.0319
-5.750 -0.3924 0.02758 0.01988 -0.0304 0.8749 0.0330
-5.500 -0.3724 0.02657 0.01879 -0.0287 0.8697 0.0336
-5.250 -0.3448 0.02557 0.01765 -0.0284 0.8669 0.0341
-5.000 -0.3141 0.02486 0.01687 -0.0287 0.8647 0.0359
-4.750 -0.2831 0.02396 0.01577 -0.0290 0.8634 0.0376
-4.500 -0.2703 0.02348 0.01515 -0.0257 0.8556 0.0381
-4.250 -0.2422 0.02274 0.01426 -0.0254 0.8522 0.0391
-4.000 -0.2079 0.02181 0.01333 -0.0264 0.8497 0.0401
-3.750 -0.1752 0.02120 0.01272 -0.0272 0.8479 0.0419
-3.500 -0.1365 0.02034 0.01180 -0.0290 0.8462 0.0436
-3.250 -0.1193 0.02004 0.01147 -0.0266 0.8385 0.0442
-3.000 -0.0889 0.01948 0.01085 -0.0268 0.8342 0.0454
-2.750 -0.0531 0.01876 0.01017 -0.0282 0.8312 0.0472
-2.500 -0.0138 0.01807 0.00949 -0.0303 0.8288 0.0495
-2.250 0.0054 0.01780 0.00920 -0.0282 0.8194 0.0514
-2.000 0.0460 0.01707 0.00844 -0.0303 0.8128 0.0538
-1.750 0.0759 0.01660 0.00796 -0.0304 0.8028 0.0569
-1.500 0.1225 0.01591 0.00723 -0.0339 0.7930 0.0627
-1.250 0.1494 0.01554 0.00685 -0.0334 0.7779 0.0710
-1.000 0.1771 0.01522 0.00655 -0.0332 0.7644 0.0822
-0.750 0.4956 0.01304 0.00714 -0.0970 0.7163 0.9590
-0.500 0.5569 0.01371 0.00726 -0.1037 0.6431 0.9832
-0.250 0.6025 0.01420 0.00720 -0.1076 0.5698 0.9929
0.000 0.6410 0.01456 0.00710 -0.1102 0.5015 1.0000
0.250 0.6479 0.01495 0.00721 -0.1059 0.4647 1.0000
0.500 0.6594 0.01525 0.00730 -0.1027 0.4423 1.0000
0.750 0.6730 0.01552 0.00741 -0.0999 0.4251 1.0000
1.000 0.6875 0.01578 0.00753 -0.0973 0.4105 1.0000
1.250 0.7032 0.01603 0.00766 -0.0949 0.3969 1.0000
1.500 0.7197 0.01625 0.00779 -0.0927 0.3835 1.0000
1.750 0.7361 0.01650 0.00793 -0.0905 0.3710 1.0000
2.000 0.7520 0.01676 0.00808 -0.0882 0.3557 1.0000
2.250 0.7691 0.01700 0.00822 -0.0862 0.3427 1.0000
2.500 0.7866 0.01724 0.00838 -0.0843 0.3302 1.0000
2.750 0.8034 0.01750 0.00855 -0.0823 0.3172 1.0000
3.000 0.8199 0.01779 0.00875 -0.0802 0.3057 1.0000
3.250 0.8367 0.01807 0.00895 -0.0782 0.2931 1.0000
3.500 0.8538 0.01837 0.00917 -0.0763 0.2829 1.0000
3.750 0.8701 0.01870 0.00942 -0.0743 0.2738 1.0000
4.000 0.8879 0.01899 0.00967 -0.0726 0.2662 1.0000
4.250 0.9045 0.01934 0.00995 -0.0706 0.2589 1.0000
4.500 0.9219 0.01967 0.01023 -0.0689 0.2526 1.0000
4.750 0.9394 0.02000 0.01053 -0.0672 0.2466 1.0000
5.000 0.9553 0.02041 0.01087 -0.0652 0.2410 1.0000
5.250 0.9734 0.02073 0.01118 -0.0637 0.2371 1.0000
5.500 0.9915 0.02107 0.01153 -0.0622 0.2326 1.0000
5.750 1.0089 0.02145 0.01189 -0.0605 0.2289 1.0000
6.000 1.0257 0.02186 0.01226 -0.0589 0.2258 1.0000
6.250 1.0427 0.02229 0.01266 -0.0572 0.2229 1.0000
6.500 1.0614 0.02264 0.01306 -0.0559 0.2204 1.0000
6.750 1.0798 0.02301 0.01345 -0.0546 0.2175 1.0000
7.000 1.0978 0.02342 0.01387 -0.0532 0.2151 1.0000
7.250 1.1151 0.02385 0.01431 -0.0518 0.2125 1.0000
7.500 1.1322 0.02433 0.01479 -0.0504 0.2104 1.0000
7.750 1.1493 0.02483 0.01527 -0.0490 0.2082 1.0000
8.000 1.1677 0.02529 0.01575 -0.0478 0.2063 1.0000
8.250 1.1862 0.02571 0.01625 -0.0466 0.2044 1.0000
8.500 1.2041 0.02615 0.01676 -0.0455 0.2024 1.0000
8.750 1.2212 0.02662 0.01727 -0.0442 0.1999 1.0000
9.000 1.2390 0.02712 0.01783 -0.0430 0.1983 1.0000
9.250 1.2562 0.02763 0.01838 -0.0418 0.1966 1.0000
9.500 1.2736 0.02817 0.01895 -0.0406 0.1951 1.0000
9.750 1.2909 0.02873 0.01953 -0.0396 0.1936 1.0000
10.000 1.3094 0.02931 0.02013 -0.0387 0.1923 1.0000
10.250 1.3281 0.02990 0.02076 -0.0379 0.1907 1.0000
10.500 1.3446 0.03046 0.02144 -0.0367 0.1895 1.0000
10.750 1.3602 0.03105 0.02214 -0.0354 0.1880 1.0000
11.000 1.3754 0.03167 0.02288 -0.0341 0.1863 1.0000
11.250 1.3909 0.03231 0.02363 -0.0329 0.1848 1.0000
11.500 1.4062 0.03298 0.02439 -0.0317 0.1833 1.0000
11.750 1.4201 0.03367 0.02516 -0.0304 0.1817 1.0000
12.000 1.4337 0.03438 0.02597 -0.0290 0.1800 1.0000
12.250 1.4468 0.03512 0.02676 -0.0277 0.1784 1.0000
12.500 1.4612 0.03589 0.02753 -0.0266 0.1762 1.0000
12.750 1.4692 0.03680 0.02859 -0.0247 0.1740 1.0000
13.000 1.4779 0.03773 0.02969 -0.0229 0.1721 1.0000
13.250 1.4845 0.03871 0.03083 -0.0210 0.1695 1.0000
13.500 1.4914 0.03974 0.03196 -0.0193 0.1669 1.0000
13.750 1.4977 0.04080 0.03312 -0.0176 0.1644 1.0000
14.000 1.5046 0.04190 0.03423 -0.0160 0.1620 1.0000
14.250 1.5086 0.04323 0.03568 -0.0143 0.1591 1.0000
14.500 1.5137 0.04459 0.03724 -0.0129 0.1569 1.0000
14.750 1.5180 0.04603 0.03885 -0.0115 0.1543 1.0000
15.000 1.5223 0.04754 0.04049 -0.0101 0.1521 1.0000
15.250 1.5237 0.04924 0.04226 -0.0088 0.1490 1.0000
15.500 1.5260 0.05096 0.04402 -0.0077 0.1467 1.0000
15.750 1.5275 0.05294 0.04622 -0.0067 0.1440 1.0000
16.000 1.5268 0.05518 0.04868 -0.0058 0.1400 1.0000
16.250 1.5267 0.05741 0.05104 -0.0051 0.1373 1.0000
16.500 1.5228 0.06011 0.05379 -0.0045 0.1338 1.0000
16.750 1.5217 0.06271 0.05659 -0.0042 0.1311 1.0000
17.000 1.5146 0.06613 0.06019 -0.0041 0.1249 1.0000
17.250 1.5058 0.06983 0.06397 -0.0043 0.1212 1.0000
17.500 1.4998 0.07335 0.06770 -0.0045 0.1176 1.0000
17.750 1.4867 0.07795 0.07244 -0.0053 0.1122 1.0000
18.000 1.4694 0.08332 0.07794 -0.0064 0.1071 1.0000
18.250 1.4425 0.09036 0.08509 -0.0083 0.0996 1.0000
18.500 1.4203 0.09682 0.09171 -0.0103 0.0974 1.0000
18.750 1.3888 0.10496 0.10001 -0.0129 0.0940 1.0000
19.000 1.3565 0.11339 0.10863 -0.0157 0.0938 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Glenn Martin 3 (glennmartin3-il)