Glenn Martin 3 (glennmartin3-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Glenn Martin 3 (glennmartin3-il) Reynolds number: 100,000 Max Cl/Cd: 41.62 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin3-il-100000.txt Download as CSV file: xf-glennmartin3-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.5521 0.08829 0.08428 -0.0021 1.0000 0.1264
-6.250 -0.5617 0.08585 0.08181 0.0004 1.0000 0.1302
-6.000 -0.6114 0.08549 0.08091 0.0039 1.0000 0.1357
-5.750 -0.5933 0.07966 0.07541 0.0054 1.0000 0.1379
-5.500 -0.5882 0.07724 0.07306 0.0084 1.0000 0.1406
-5.250 -0.5894 0.07505 0.07084 0.0113 1.0000 0.1454
-5.000 -0.6091 0.07288 0.06828 0.0149 1.0000 0.1531
-4.750 -0.6014 0.06973 0.06529 0.0176 1.0000 0.1558
-4.500 -0.5982 0.06773 0.06329 0.0207 1.0000 0.1604
-4.250 -0.6064 0.06547 0.06082 0.0247 1.0000 0.1719
-4.000 -0.5827 0.06375 0.05908 0.0243 0.9945 0.1810
-3.750 -0.5383 0.06105 0.05596 0.0193 0.9684 0.2061
-3.500 -0.5143 0.05878 0.05352 0.0194 0.9534 0.2237
-3.250 -0.4871 0.05590 0.05071 0.0191 0.9441 0.2323
-3.000 -0.4820 0.04559 0.03810 0.0283 0.9351 0.1085
-2.750 -0.4579 0.04304 0.03517 0.0300 0.9253 0.1010
-2.500 -0.4285 0.04012 0.03146 0.0315 0.9162 0.0955
-2.250 -0.3897 0.03875 0.02982 0.0299 0.9078 0.0971
-2.000 -0.3558 0.03726 0.02797 0.0294 0.8975 0.0971
-1.750 -0.3008 0.03601 0.02647 0.0248 0.8907 0.0996
-1.500 -0.2582 0.03498 0.02527 0.0223 0.8803 0.1036
-1.250 0.1777 0.03122 0.02515 -0.0612 0.9038 1.0000
-1.000 0.2323 0.03047 0.02403 -0.0655 0.8926 1.0000
-0.750 0.2752 0.02965 0.02297 -0.0676 0.8789 1.0000
-0.500 0.3135 0.02894 0.02209 -0.0690 0.8659 1.0000
-0.250 0.3543 0.02818 0.02118 -0.0707 0.8544 1.0000
0.000 0.4061 0.02709 0.01993 -0.0743 0.8462 1.0000
0.250 0.4417 0.02621 0.01897 -0.0748 0.8324 1.0000
0.500 0.4804 0.02520 0.01787 -0.0758 0.8197 1.0000
0.750 0.5360 0.02354 0.01611 -0.0795 0.8120 1.0000
1.000 0.5744 0.02242 0.01492 -0.0803 0.7955 1.0000
1.250 0.6070 0.02154 0.01399 -0.0802 0.7733 1.0000
1.500 0.6453 0.02057 0.01292 -0.0810 0.7441 1.0000
1.750 0.6816 0.01981 0.01198 -0.0816 0.6984 1.0000
2.000 0.7549 0.01882 0.01041 -0.0897 0.6240 1.0000
2.250 0.7931 0.01910 0.01013 -0.0915 0.5604 1.0000
2.500 0.8162 0.01961 0.01023 -0.0906 0.5163 1.0000
2.750 0.8383 0.02018 0.01044 -0.0896 0.4828 1.0000
3.000 0.8632 0.02084 0.01075 -0.0892 0.4547 1.0000
3.250 0.8891 0.02155 0.01120 -0.0891 0.4293 1.0000
3.500 0.9164 0.02224 0.01168 -0.0894 0.4094 1.0000
3.750 0.9433 0.02293 0.01218 -0.0896 0.3922 1.0000
4.000 0.9707 0.02360 0.01271 -0.0899 0.3778 1.0000
4.250 0.9949 0.02417 0.01316 -0.0895 0.3658 1.0000
4.500 1.0185 0.02477 0.01375 -0.0890 0.3557 1.0000
4.750 1.0547 0.02554 0.01433 -0.0913 0.3463 1.0000
5.000 1.0715 0.02605 0.01495 -0.0893 0.3386 1.0000
5.250 1.1019 0.02671 0.01551 -0.0904 0.3318 1.0000
5.500 1.1276 0.02742 0.01624 -0.0904 0.3251 1.0000
5.750 1.1488 0.02802 0.01691 -0.0894 0.3191 1.0000
6.000 1.1825 0.02876 0.01750 -0.0913 0.3131 1.0000
6.250 1.2027 0.02950 0.01837 -0.0902 0.3087 1.0000
6.500 1.2221 0.03022 0.01922 -0.0889 0.3043 1.0000
6.750 1.2468 0.03095 0.01996 -0.0888 0.3001 1.0000
7.000 1.2807 0.03184 0.02079 -0.0908 0.2966 1.0000
7.250 1.3009 0.03281 0.02192 -0.0898 0.2935 1.0000
7.500 1.3145 0.03369 0.02300 -0.0875 0.2902 1.0000
7.750 1.3300 0.03452 0.02395 -0.0856 0.2866 1.0000
8.000 1.3509 0.03541 0.02492 -0.0848 0.2835 1.0000
8.250 1.3797 0.03638 0.02587 -0.0858 0.2804 1.0000
8.500 1.3999 0.03765 0.02727 -0.0851 0.2782 1.0000
8.750 1.4037 0.03887 0.02877 -0.0811 0.2762 1.0000
9.000 1.4087 0.04017 0.03030 -0.0774 0.2740 1.0000
9.250 1.4151 0.04150 0.03185 -0.0740 0.2719 1.0000
9.500 1.4251 0.04269 0.03319 -0.0714 0.2693 1.0000
9.750 1.4401 0.04383 0.03443 -0.0698 0.2668 1.0000
10.000 1.4616 0.04505 0.03568 -0.0696 0.2645 1.0000
10.250 1.4796 0.04680 0.03754 -0.0689 0.2623 1.0000
10.500 1.4580 0.04849 0.03955 -0.0607 0.2608 1.0000
10.750 1.4343 0.05012 0.04144 -0.0524 0.2593 1.0000
11.000 1.4113 0.05225 0.04382 -0.0448 0.2582 1.0000
11.250 1.3837 0.05455 0.04637 -0.0371 0.2564 1.0000
11.500 1.3533 0.05748 0.04952 -0.0299 0.2552 1.0000
11.750 1.3124 0.06130 0.05358 -0.0224 0.2540 1.0000
12.000 0.9084 0.11398 0.10671 -0.0186 0.2628 1.0000
12.250 0.7692 0.14674 0.13954 -0.0328 0.3133 1.0000
12.500 1.3866 0.06491 0.05728 -0.0236 0.2463 1.0000
12.750 1.3122 0.07113 0.06376 -0.0143 0.2461 1.0000
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Polar data table (+)
Polar graphs
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