Glenn Martin 2 (glennmartin2-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: Glenn Martin 2 (glennmartin2-il) Reynolds number: 200,000 Max Cl/Cd: 58.68 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin2-il-200000.txt Download as CSV file: xf-glennmartin2-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2262 0.11373 0.11062 -0.0402 0.9882 0.0499
-10.000 -0.2238 0.10984 0.10675 -0.0495 0.9840 0.0526
-9.750 -0.2248 0.10600 0.10294 -0.0568 0.9771 0.0530
-9.500 -0.2061 0.10010 0.09704 -0.0588 0.9742 0.0537
-9.250 -0.1756 0.09652 0.09342 -0.0590 0.9725 0.0552
-9.000 -0.1586 0.09335 0.09025 -0.0612 0.9672 0.0575
-8.750 -0.0527 0.07271 0.06975 -0.0803 0.9456 0.0650
-8.500 -0.0256 0.06856 0.06558 -0.0827 0.9437 0.0671
-8.250 -0.0224 0.06548 0.06251 -0.0833 0.9346 0.0692
-8.000 -0.1376 0.07584 0.07274 -0.0821 0.9358 0.0650
-7.750 -0.1114 0.07258 0.06947 -0.0839 0.9321 0.0669
-7.500 -0.0856 0.06831 0.06514 -0.0893 0.9290 0.0699
-7.250 -0.0833 0.06301 0.05951 -0.0980 0.9152 0.0754
-7.000 -0.0818 0.05761 0.05409 -0.0974 0.9059 0.0766
-6.750 -0.0528 0.05527 0.05181 -0.0979 0.9029 0.0786
-6.500 -0.0210 0.05199 0.04845 -0.1011 0.9000 0.0817
-6.250 -0.0413 0.03842 0.03407 -0.1004 0.8863 0.0614
-6.000 -0.0202 0.03240 0.02746 -0.1014 0.8827 0.0604
-5.750 -0.0159 0.02918 0.02379 -0.0973 0.8707 0.0606
-5.500 0.0144 0.02566 0.01961 -0.0979 0.8670 0.0617
-5.250 0.0283 0.02430 0.01781 -0.0946 0.8551 0.0637
-5.000 0.0619 0.02208 0.01542 -0.0959 0.8493 0.0663
-4.750 0.0868 0.02103 0.01422 -0.0949 0.8385 0.0687
-4.500 0.1130 0.02015 0.01312 -0.0941 0.8277 0.0723
-4.250 0.1504 0.01923 0.01184 -0.0953 0.8197 0.0755
-4.000 0.1731 0.01779 0.01030 -0.0941 0.8070 0.0789
-3.750 0.1994 0.01722 0.00968 -0.0934 0.7947 0.0843
-3.500 0.2285 0.01672 0.00896 -0.0931 0.7827 0.0894
-3.250 0.2593 0.01562 0.00785 -0.0936 0.7704 0.0971
-3.000 0.2871 0.01505 0.00716 -0.0932 0.7561 0.1067
-2.750 0.3124 0.01451 0.00662 -0.0924 0.7404 0.1176
-2.500 0.3365 0.01404 0.00612 -0.0914 0.7237 0.1284
-2.250 0.3603 0.01375 0.00577 -0.0902 0.7060 0.1401
-2.000 0.3841 0.01355 0.00552 -0.0891 0.6876 0.1535
-1.750 0.4073 0.01345 0.00538 -0.0880 0.6685 0.1719
-1.500 0.4302 0.01345 0.00533 -0.0867 0.6484 0.1997
-1.250 0.4498 0.01356 0.00542 -0.0847 0.6267 0.2401
-1.000 0.4677 0.01375 0.00547 -0.0824 0.6027 0.2736
-0.750 0.4823 0.01387 0.00547 -0.0795 0.5746 0.2951
-0.500 0.4944 0.01393 0.00542 -0.0761 0.5407 0.3108
-0.250 0.5053 0.01404 0.00534 -0.0725 0.5053 0.3243
0.000 0.5167 0.01415 0.00529 -0.0692 0.4786 0.3364
0.250 0.5302 0.01430 0.00530 -0.0663 0.4606 0.3492
0.500 0.5461 0.01441 0.00535 -0.0639 0.4481 0.3662
0.750 0.5635 0.01453 0.00543 -0.0619 0.4391 0.3893
1.000 0.5783 0.01427 0.00550 -0.0594 0.4314 0.4953
1.250 0.8357 0.01533 0.00702 -0.1088 0.4112 1.0000
1.500 0.8587 0.01564 0.00720 -0.1080 0.4069 1.0000
1.750 0.8797 0.01587 0.00738 -0.1068 0.4029 1.0000
2.000 0.9012 0.01612 0.00757 -0.1057 0.3988 1.0000
2.250 0.9241 0.01643 0.00777 -0.1050 0.3950 1.0000
2.500 0.9495 0.01681 0.00802 -0.1048 0.3916 1.0000
2.750 0.9700 0.01704 0.00826 -0.1035 0.3886 1.0000
3.000 0.9917 0.01730 0.00852 -0.1025 0.3856 1.0000
3.250 1.0144 0.01760 0.00878 -0.1017 0.3828 1.0000
3.500 1.0383 0.01792 0.00905 -0.1012 0.3801 1.0000
3.750 1.0644 0.01832 0.00937 -0.1012 0.3776 1.0000
4.000 1.0903 0.01876 0.00978 -0.1012 0.3752 1.0000
4.250 1.1094 0.01903 0.01012 -0.0997 0.3727 1.0000
4.500 1.1295 0.01933 0.01046 -0.0984 0.3698 1.0000
4.750 1.1510 0.01966 0.01080 -0.0975 0.3669 1.0000
5.000 1.1736 0.02000 0.01111 -0.0968 0.3637 1.0000
5.250 1.2018 0.02054 0.01153 -0.0973 0.3602 1.0000
5.500 1.2174 0.02083 0.01192 -0.0952 0.3572 1.0000
5.750 1.2339 0.02111 0.01230 -0.0933 0.3538 1.0000
6.000 1.2536 0.02145 0.01267 -0.0921 0.3508 1.0000
6.250 1.2759 0.02183 0.01306 -0.0914 0.3482 1.0000
6.500 1.3014 0.02228 0.01349 -0.0914 0.3457 1.0000
6.750 1.3261 0.02285 0.01407 -0.0914 0.3428 1.0000
7.000 1.3356 0.02307 0.01444 -0.0881 0.3391 1.0000
7.250 1.3480 0.02326 0.01469 -0.0854 0.3344 1.0000
7.500 1.3683 0.02346 0.01480 -0.0844 0.3293 1.0000
7.750 1.3801 0.02380 0.01522 -0.0817 0.3249 1.0000
8.000 1.3875 0.02400 0.01553 -0.0782 0.3204 1.0000
8.250 1.3996 0.02413 0.01565 -0.0755 0.3154 1.0000
8.500 1.4175 0.02445 0.01593 -0.0741 0.3107 1.0000
8.750 1.4164 0.02465 0.01629 -0.0689 0.3070 1.0000
9.000 1.4197 0.02480 0.01652 -0.0647 0.3026 1.0000
9.250 1.4280 0.02489 0.01658 -0.0615 0.2977 1.0000
9.500 1.4276 0.02514 0.01692 -0.0569 0.2922 1.0000
9.750 1.4281 0.02539 0.01728 -0.0526 0.2866 1.0000
10.000 1.4354 0.02566 0.01754 -0.0497 0.2816 1.0000
10.250 1.4383 0.02613 0.01816 -0.0462 0.2762 1.0000
10.500 1.4412 0.02660 0.01874 -0.0429 0.2701 1.0000
10.750 1.4448 0.02715 0.01930 -0.0400 0.2636 1.0000
11.000 1.4471 0.02785 0.02015 -0.0370 0.2550 1.0000
11.250 1.4495 0.02868 0.02104 -0.0343 0.2444 1.0000
11.500 1.4534 0.02963 0.02205 -0.0320 0.2343 1.0000
11.750 1.4568 0.03076 0.02322 -0.0299 0.2196 1.0000
12.000 1.4582 0.03216 0.02461 -0.0278 0.2027 1.0000
12.250 1.4536 0.03409 0.02646 -0.0254 0.1850 1.0000
12.500 1.4391 0.03699 0.02921 -0.0227 0.1644 1.0000
12.750 1.4275 0.03995 0.03212 -0.0206 0.1487 1.0000
13.000 1.4190 0.04288 0.03505 -0.0191 0.1364 1.0000
13.250 1.4090 0.04616 0.03834 -0.0179 0.1235 1.0000
13.500 1.3964 0.04990 0.04209 -0.0170 0.1099 1.0000
13.750 1.3756 0.05475 0.04690 -0.0163 0.0923 1.0000
14.000 1.3516 0.06025 0.05240 -0.0161 0.0744 1.0000
14.250 1.3230 0.06661 0.05877 -0.0163 0.0584 1.0000
14.500 1.3026 0.07230 0.06454 -0.0170 0.0490 1.0000
14.750 1.2764 0.07905 0.07136 -0.0180 0.0382 1.0000
15.000 1.2544 0.08547 0.07786 -0.0193 0.0334 1.0000
15.250 1.2378 0.09122 0.08372 -0.0205 0.0309 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Glenn Martin 2 (glennmartin2-il)