Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Glenn Martin 4 (glennmartin4-il) Reynolds number: 50,000 Max Cl/Cd: 22.01 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin4-il-50000.txt Download as CSV file: xf-glennmartin4-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: Glenn Martin 4
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3635 0.11483 0.10953 -0.0118 1.0000 0.2252
-7.000 -0.3888 0.11373 0.10857 -0.0102 1.0000 0.2322
-6.750 -0.4293 0.11336 0.10838 -0.0080 1.0000 0.2338
-6.500 -0.4032 0.10914 0.10419 -0.0057 1.0000 0.2467
-6.250 -0.4439 0.10877 0.10399 -0.0026 1.0000 0.2499
-6.000 -0.4355 0.10562 0.10091 0.0000 1.0000 0.2617
-5.750 -0.4665 0.10490 0.10033 0.0031 1.0000 0.2655
-5.500 -0.5099 0.10454 0.10008 0.0046 1.0000 0.2683
-5.250 -0.5015 0.10174 0.09739 0.0085 1.0000 0.2829
-5.000 -0.5078 0.09974 0.09549 0.0115 1.0000 0.2924
-4.750 -0.5470 0.09921 0.09499 0.0128 1.0000 0.3023
-4.500 -0.5417 0.09691 0.09280 0.0167 1.0000 0.3169
-4.250 -0.5164 0.09506 0.09090 0.0131 0.9833 0.3707
-3.750 0.0169 0.08248 0.07747 -0.0179 1.0000 1.0000
-3.500 -0.0274 0.07924 0.07443 -0.0115 0.9549 0.9008
-3.250 -0.1149 0.07893 0.07431 -0.0008 0.9305 0.7991
-3.000 -0.1994 0.07719 0.07275 0.0060 0.9108 0.7157
-2.750 -0.2712 0.07538 0.07111 0.0136 0.8938 0.6800
-2.500 -0.3375 0.07285 0.06867 0.0199 0.8784 0.6462
-2.250 -0.3309 0.06078 0.05341 -0.0157 0.8632 0.1961
-2.000 -0.3058 0.05801 0.05004 -0.0147 0.8498 0.1764
-1.750 -0.2826 0.05658 0.04767 -0.0126 0.8370 0.1664
-1.500 -0.2491 0.05431 0.04495 -0.0128 0.8257 0.1673
-1.250 -0.2186 0.05272 0.04286 -0.0124 0.8126 0.1663
-1.000 -0.1942 0.05137 0.04125 -0.0117 0.7989 0.1678
-0.750 -0.1617 0.05000 0.03975 -0.0124 0.7850 0.1767
-0.500 0.2480 0.04044 0.03262 -0.0802 0.7810 1.0000
-0.250 0.2809 0.04029 0.03180 -0.0803 0.7662 1.0000
0.000 0.3118 0.04013 0.03121 -0.0804 0.7521 1.0000
0.250 0.3802 0.03817 0.02873 -0.0854 0.7458 1.0000
0.500 0.4089 0.03800 0.02831 -0.0852 0.7311 1.0000
0.750 0.4370 0.03796 0.02802 -0.0850 0.7169 1.0000
1.000 0.4683 0.03779 0.02761 -0.0852 0.7036 1.0000
1.250 0.5601 0.03510 0.02453 -0.0944 0.6974 1.0000
1.500 0.5860 0.03537 0.02463 -0.0940 0.6830 1.0000
1.750 0.6129 0.03569 0.02478 -0.0939 0.6692 1.0000
2.000 0.6470 0.03581 0.02474 -0.0949 0.6568 1.0000
2.250 0.7353 0.03450 0.02311 -0.1053 0.6462 1.0000
2.500 0.7517 0.03534 0.02386 -0.1035 0.6338 1.0000
2.750 0.7361 0.03718 0.02570 -0.0964 0.6223 1.0000
3.000 0.8078 0.03670 0.02500 -0.1043 0.6126 1.0000
3.250 0.7658 0.03932 0.02769 -0.0928 0.6027 1.0000
3.500 0.7881 0.04031 0.02860 -0.0923 0.5946 1.0000
3.750 0.7251 0.04448 0.03288 -0.0790 0.5852 1.0000
4.000 0.5736 0.05631 0.04498 -0.0602 0.5717 1.0000
4.250 0.6238 0.05506 0.04358 -0.0618 0.5666 1.0000
4.500 0.7795 0.04801 0.03624 -0.0760 0.5639 1.0000
4.750 0.4925 0.07151 0.06023 -0.0509 0.5558 1.0000
5.000 0.4852 0.07505 0.06376 -0.0494 0.5529 1.0000
5.250 0.5370 0.07428 0.06285 -0.0506 0.5468 1.0000
5.500 0.5127 0.07935 0.06794 -0.0487 0.5464 1.0000
5.750 0.5101 0.08301 0.07160 -0.0480 0.5470 1.0000
6.000 0.3206 0.09973 0.08888 -0.0442 0.6915 1.0000
6.250 0.3429 0.10209 0.09115 -0.0450 0.6827 1.0000
6.500 0.3439 0.10370 0.09273 -0.0435 0.6743 1.0000
6.750 0.3731 0.10647 0.09542 -0.0449 0.6653 1.0000
7.000 0.3683 0.10759 0.09651 -0.0428 0.6551 1.0000
7.250 0.4059 0.11130 0.10016 -0.0452 0.6478 1.0000
7.500 0.3942 0.11166 0.10051 -0.0424 0.6365 1.0000
7.750 0.4276 0.11555 0.10435 -0.0445 0.6310 1.0000
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Polar data table (+)
Polar graphs
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