Glenn Martin 3 (glennmartin3-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Glenn Martin 3 (glennmartin3-il) Reynolds number: 50,000 Max Cl/Cd: 29.07 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-glennmartin3-il-50000-n5.txt Download as CSV file: xf-glennmartin3-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4980 0.09662 0.09051 -0.0215 1.0000 0.0716
-7.500 -0.5106 0.09377 0.08768 -0.0192 1.0000 0.0712
-7.250 -0.5236 0.09063 0.08454 -0.0168 1.0000 0.0707
-7.000 -0.5353 0.08748 0.08137 -0.0143 1.0000 0.0702
-6.750 -0.5463 0.08416 0.07800 -0.0117 1.0000 0.0696
-6.500 -0.5513 0.08060 0.07436 -0.0100 0.9986 0.0684
-6.250 -0.5468 0.07614 0.06970 -0.0104 0.9929 0.0670
-6.000 -0.5433 0.07161 0.06489 -0.0100 0.9870 0.0659
-5.750 -0.5384 0.06801 0.06102 -0.0086 0.9811 0.0663
-5.500 -0.5310 0.06480 0.05753 -0.0071 0.9752 0.0670
-5.250 -0.5228 0.06170 0.05411 -0.0051 0.9694 0.0675
-5.000 -0.5172 0.05866 0.05070 -0.0022 0.9630 0.0686
-4.750 -0.5073 0.05578 0.04742 0.0003 0.9573 0.0687
-4.500 -0.4976 0.05325 0.04449 0.0033 0.9509 0.0688
-4.250 -0.4867 0.05087 0.04158 0.0064 0.9448 0.0706
-4.000 -0.4722 0.04871 0.03883 0.0091 0.9386 0.0720
-3.750 -0.4558 0.04686 0.03658 0.0113 0.9323 0.0733
-3.500 -0.4313 0.04521 0.03468 0.0120 0.9260 0.0746
-3.250 -0.4064 0.04387 0.03310 0.0126 0.9179 0.0762
-3.000 -0.3697 0.04254 0.03145 0.0112 0.9106 0.0799
-2.750 -0.3370 0.04106 0.02954 0.0107 0.9000 0.0825
-2.500 -0.2900 0.03959 0.02773 0.0074 0.8908 0.0848
-2.250 -0.2429 0.03849 0.02661 0.0037 0.8823 0.0907
-2.000 -0.1851 0.03748 0.02536 -0.0020 0.8754 0.0971
-1.750 -0.1236 0.03670 0.02455 -0.0089 0.8685 0.1050
-1.500 -0.0612 0.03604 0.02386 -0.0157 0.8632 0.1197
-1.250 0.1916 0.03411 0.02520 -0.0619 0.8743 1.0000
-1.000 0.2282 0.03386 0.02459 -0.0633 0.8642 1.0000
-0.750 0.2546 0.03368 0.02414 -0.0628 0.8509 1.0000
-0.500 0.2859 0.03340 0.02362 -0.0632 0.8383 1.0000
-0.250 0.3281 0.03281 0.02279 -0.0652 0.8277 1.0000
0.000 0.3572 0.03235 0.02215 -0.0648 0.8116 1.0000
0.250 0.3876 0.03178 0.02144 -0.0646 0.7948 1.0000
0.500 0.4179 0.03112 0.02063 -0.0641 0.7770 1.0000
1.000 0.4639 0.03033 0.01961 -0.0609 0.7331 1.0000
1.250 0.4904 0.02986 0.01903 -0.0599 0.7103 1.0000
1.500 0.5156 0.02947 0.01852 -0.0586 0.6830 1.0000
1.750 0.5535 0.02868 0.01755 -0.0594 0.6580 1.0000
2.000 0.5905 0.02807 0.01670 -0.0601 0.6278 1.0000
2.250 0.6301 0.02754 0.01586 -0.0613 0.5931 1.0000
2.500 0.6626 0.02743 0.01542 -0.0617 0.5574 1.0000
2.750 0.6893 0.02759 0.01528 -0.0612 0.5244 1.0000
3.000 0.7134 0.02791 0.01529 -0.0604 0.4959 1.0000
3.250 0.7355 0.02834 0.01543 -0.0594 0.4711 1.0000
3.500 0.7576 0.02883 0.01565 -0.0584 0.4507 1.0000
3.750 0.7796 0.02936 0.01598 -0.0575 0.4324 1.0000
4.000 0.8018 0.02991 0.01637 -0.0568 0.4158 1.0000
4.250 0.8241 0.03048 0.01681 -0.0561 0.4003 1.0000
4.500 0.8470 0.03106 0.01728 -0.0555 0.3860 1.0000
4.750 0.8729 0.03161 0.01770 -0.0555 0.3744 1.0000
5.000 0.8960 0.03220 0.01828 -0.0550 0.3623 1.0000
5.250 0.9216 0.03278 0.01882 -0.0550 0.3526 1.0000
5.500 0.9464 0.03336 0.01934 -0.0548 0.3430 1.0000
5.750 0.9690 0.03399 0.01998 -0.0543 0.3343 1.0000
6.000 0.9936 0.03461 0.02058 -0.0542 0.3267 1.0000
6.250 1.0162 0.03527 0.02123 -0.0537 0.3195 1.0000
6.500 1.0388 0.03599 0.02203 -0.0533 0.3132 1.0000
6.750 1.0651 0.03664 0.02262 -0.0535 0.3078 1.0000
7.000 1.0882 0.03748 0.02354 -0.0533 0.3028 1.0000
7.250 1.1070 0.03832 0.02450 -0.0523 0.2976 1.0000
7.500 1.1300 0.03912 0.02532 -0.0520 0.2931 1.0000
7.750 1.1551 0.03990 0.02608 -0.0521 0.2890 1.0000
8.000 1.1665 0.04098 0.02736 -0.0500 0.2845 1.0000
8.250 1.1816 0.04199 0.02852 -0.0484 0.2804 1.0000
8.500 1.2006 0.04293 0.02953 -0.0476 0.2770 1.0000
8.750 1.2260 0.04386 0.03047 -0.0479 0.2742 1.0000
9.000 1.2392 0.04513 0.03190 -0.0463 0.2715 1.0000
9.250 1.2420 0.04666 0.03370 -0.0430 0.2684 1.0000
9.500 1.2473 0.04812 0.03536 -0.0402 0.2655 1.0000
9.750 1.2552 0.04948 0.03687 -0.0380 0.2627 1.0000
10.000 1.2682 0.05068 0.03816 -0.0364 0.2600 1.0000
10.250 1.2880 0.05181 0.03933 -0.0360 0.2576 1.0000
10.500 1.2871 0.05361 0.04134 -0.0327 0.2553 1.0000
10.750 1.2694 0.05619 0.04421 -0.0275 0.2534 1.0000
11.000 1.2485 0.05918 0.04748 -0.0225 0.2513 1.0000
11.250 1.2235 0.06267 0.05122 -0.0178 0.2493 1.0000
11.500 1.1919 0.06705 0.05584 -0.0135 0.2474 1.0000
11.750 1.1547 0.07240 0.06136 -0.0100 0.2453 1.0000
12.000 1.1438 0.07592 0.06499 -0.0085 0.2427 1.0000
12.250 1.1293 0.08021 0.06942 -0.0073 0.2410 1.0000
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Polar data table (+)
Polar graphs
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