Glenn Martin 3 (glennmartin3-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Glenn Martin 3 (glennmartin3-il) Reynolds number: 50,000 Max Cl/Cd: 32.45 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin3-il-50000.txt Download as CSV file: xf-glennmartin3-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-4.000 -0.2513 0.07270 0.06738 0.0346 1.0000 0.7917
-3.750 -0.3042 0.07102 0.06589 0.0417 1.0000 0.7562
-3.500 -0.3721 0.06901 0.06408 0.0498 1.0000 0.7179
-3.250 -0.4460 0.06744 0.06273 0.0610 1.0000 0.7099
-3.000 -0.5879 0.05931 0.05233 0.0418 1.0000 0.2582
-2.750 -0.5696 0.05377 0.04582 0.0438 1.0000 0.1841
-2.500 -0.5616 0.05123 0.04310 0.0472 1.0000 0.1774
-2.250 -0.5528 0.04920 0.04045 0.0512 1.0000 0.1656
-2.000 -0.5422 0.04730 0.03830 0.0542 1.0000 0.1610
-1.750 -0.5311 0.04570 0.03631 0.0573 1.0000 0.1581
-1.500 -0.5179 0.04439 0.03464 0.0598 1.0000 0.1571
-1.250 -0.5034 0.04335 0.03336 0.0619 1.0000 0.1591
-1.000 -0.4859 0.04233 0.03204 0.0633 1.0000 0.1592
-0.750 -0.4652 0.04146 0.03090 0.0639 1.0000 0.1592
-0.500 -0.4434 0.04090 0.03012 0.0638 1.0000 0.1623
-0.250 0.0620 0.04286 0.03406 -0.0287 0.9639 1.0000
0.000 0.1239 0.04329 0.03409 -0.0361 0.9353 1.0000
0.250 0.1852 0.04337 0.03388 -0.0426 0.9077 1.0000
0.500 0.2430 0.04299 0.03327 -0.0479 0.8793 1.0000
0.750 0.2966 0.04236 0.03245 -0.0520 0.8516 1.0000
1.000 0.3604 0.04129 0.03121 -0.0573 0.8292 1.0000
1.250 0.4022 0.04043 0.03025 -0.0588 0.8018 1.0000
1.500 0.4594 0.03888 0.02859 -0.0622 0.7802 1.0000
1.750 0.5185 0.03689 0.02651 -0.0655 0.7607 1.0000
2.000 0.5556 0.03559 0.02515 -0.0654 0.7338 1.0000
2.250 0.6195 0.03307 0.02254 -0.0689 0.7126 1.0000
2.500 0.6766 0.03104 0.02040 -0.0717 0.6842 1.0000
2.750 0.7528 0.02891 0.01799 -0.0782 0.6484 1.0000
3.000 0.8267 0.02812 0.01675 -0.0856 0.6024 1.0000
3.250 0.8865 0.02851 0.01674 -0.0914 0.5591 1.0000
3.500 0.9278 0.02931 0.01727 -0.0941 0.5282 1.0000
3.750 0.9712 0.03013 0.01779 -0.0973 0.5021 1.0000
4.000 1.0025 0.03109 0.01863 -0.0983 0.4823 1.0000
4.250 1.0370 0.03211 0.01953 -0.1000 0.4660 1.0000
4.500 1.0765 0.03317 0.02045 -0.1028 0.4521 1.0000
4.750 1.0890 0.03432 0.02170 -0.1001 0.4409 1.0000
5.000 1.1151 0.03551 0.02286 -0.1003 0.4309 1.0000
5.250 1.1330 0.03665 0.02406 -0.0988 0.4220 1.0000
5.500 1.1553 0.03800 0.02541 -0.0983 0.4143 1.0000
5.750 1.1609 0.03942 0.02704 -0.0946 0.4082 1.0000
6.000 1.1851 0.04076 0.02838 -0.0945 0.4018 1.0000
6.250 1.1951 0.04237 0.03011 -0.0918 0.3971 1.0000
6.500 1.1868 0.04419 0.03217 -0.0858 0.3930 1.0000
6.750 1.1898 0.04587 0.03401 -0.0819 0.3880 1.0000
7.000 1.2167 0.04727 0.03539 -0.0824 0.3830 1.0000
7.250 1.2116 0.04941 0.03770 -0.0774 0.3798 1.0000
7.500 1.1849 0.05201 0.04056 -0.0689 0.3776 1.0000
7.750 1.1533 0.05486 0.04362 -0.0601 0.3761 1.0000
8.000 1.1051 0.05823 0.04717 -0.0495 0.3753 1.0000
8.250 1.0177 0.06457 0.05370 -0.0364 0.3757 1.0000
8.500 0.8770 0.08012 0.06935 -0.0280 0.3801 1.0000
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Polar data table (+)
Polar graphs
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