Glenn Martin 3 (glennmartin3-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Glenn Martin 3 (glennmartin3-il) Reynolds number: 200,000 Max Cl/Cd: 54.79 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin3-il-200000.txt Download as CSV file: xf-glennmartin3-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3140 0.09246 0.08954 -0.0342 0.9822 0.0623
-8.250 -0.3113 0.08800 0.08508 -0.0372 0.9783 0.0640
-8.000 -0.5127 0.08799 0.08475 -0.0341 0.9821 0.0591
-7.750 -0.4861 0.08604 0.08291 -0.0328 0.9797 0.0601
-7.500 -0.4717 0.08350 0.08036 -0.0334 0.9755 0.0613
-7.250 -0.4687 0.08037 0.07719 -0.0333 0.9689 0.0625
-7.000 -0.4680 0.07672 0.07345 -0.0333 0.9620 0.0645
-6.750 -0.5065 0.07170 0.06764 -0.0295 0.9501 0.0688
-6.500 -0.4868 0.06601 0.06216 -0.0310 0.9468 0.0699
-6.250 -0.4670 0.06414 0.06039 -0.0306 0.9413 0.0715
-6.000 -0.4542 0.06169 0.05786 -0.0295 0.9356 0.0733
-5.750 -0.4700 0.05785 0.05338 -0.0234 0.9258 0.0811
-5.500 -0.4455 0.05484 0.05049 -0.0242 0.9222 0.0826
-5.250 -0.4315 0.05294 0.04858 -0.0223 0.9158 0.0848
-5.000 -0.4168 0.05085 0.04631 -0.0204 0.9098 0.0887
-4.750 -0.4008 0.04772 0.04287 -0.0187 0.9065 0.0963
-4.500 -0.3982 0.04638 0.04148 -0.0142 0.8971 0.0981
-4.250 -0.3744 0.04446 0.03939 -0.0135 0.8933 0.1108
-4.000 -0.3965 0.03587 0.02927 0.0009 0.8839 0.0657
-3.750 -0.3720 0.03291 0.02577 0.0029 0.8799 0.0622
-3.500 -0.3357 0.03086 0.02326 0.0024 0.8777 0.0616
-3.250 -0.3202 0.02988 0.02210 0.0052 0.8687 0.0621
-3.000 -0.2790 0.02845 0.02043 0.0034 0.8652 0.0627
-2.750 -0.2300 0.02711 0.01892 -0.0001 0.8630 0.0639
-2.500 -0.1804 0.02608 0.01775 -0.0038 0.8615 0.0668
-2.250 -0.1621 0.02559 0.01718 -0.0017 0.8515 0.0676
-2.000 -0.1061 0.02422 0.01579 -0.0069 0.8492 0.0699
-1.750 -0.0507 0.02296 0.01466 -0.0121 0.8473 0.0755
-1.500 0.0100 0.02156 0.01326 -0.0178 0.8455 0.0805
-1.250 0.3321 0.01769 0.01285 -0.0800 0.8625 0.9726
-1.000 0.4524 0.01730 0.01227 -0.0987 0.8626 1.0000
-0.750 0.4784 0.01681 0.01169 -0.0978 0.8519 1.0000
-0.500 0.5274 0.01586 0.01061 -0.1016 0.8456 1.0000
-0.250 0.5585 0.01536 0.01003 -0.1018 0.8317 1.0000
0.000 0.6012 0.01474 0.00928 -0.1044 0.8158 1.0000
0.250 0.6496 0.01417 0.00857 -0.1084 0.7962 1.0000
0.500 0.6820 0.01390 0.00816 -0.1091 0.7654 1.0000
0.750 0.7151 0.01369 0.00773 -0.1099 0.7172 1.0000
1.000 0.7512 0.01371 0.00720 -0.1113 0.6337 1.0000
1.250 0.7614 0.01417 0.00720 -0.1075 0.5710 1.0000
1.500 0.7662 0.01467 0.00735 -0.1027 0.5186 1.0000
1.750 0.7726 0.01515 0.00754 -0.0983 0.4808 1.0000
2.000 0.7817 0.01562 0.00776 -0.0946 0.4534 1.0000
2.250 0.7947 0.01605 0.00799 -0.0917 0.4312 1.0000
2.500 0.8089 0.01645 0.00823 -0.0891 0.4111 1.0000
2.750 0.8241 0.01682 0.00847 -0.0867 0.3933 1.0000
3.000 0.8390 0.01720 0.00873 -0.0843 0.3759 1.0000
3.250 0.8536 0.01757 0.00898 -0.0818 0.3584 1.0000
3.500 0.8692 0.01795 0.00924 -0.0795 0.3446 1.0000
3.750 0.8849 0.01830 0.00950 -0.0773 0.3309 1.0000
4.000 0.9018 0.01864 0.00977 -0.0753 0.3184 1.0000
4.250 0.9192 0.01903 0.01006 -0.0735 0.3088 1.0000
4.500 0.9372 0.01938 0.01035 -0.0718 0.3000 1.0000
4.750 0.9562 0.01979 0.01068 -0.0704 0.2922 1.0000
5.000 0.9748 0.02014 0.01099 -0.0688 0.2849 1.0000
5.250 0.9960 0.02061 0.01133 -0.0680 0.2792 1.0000
5.500 1.0152 0.02093 0.01170 -0.0665 0.2732 1.0000
5.750 1.0354 0.02130 0.01204 -0.0654 0.2682 1.0000
6.000 1.0596 0.02181 0.01241 -0.0652 0.2633 1.0000
6.250 1.0815 0.02219 0.01284 -0.0644 0.2598 1.0000
6.500 1.1029 0.02258 0.01327 -0.0635 0.2559 1.0000
6.750 1.1247 0.02300 0.01368 -0.0628 0.2522 1.0000
7.000 1.1494 0.02345 0.01411 -0.0627 0.2494 1.0000
7.250 1.1822 0.02410 0.01467 -0.0644 0.2459 1.0000
7.500 1.2017 0.02451 0.01519 -0.0632 0.2435 1.0000
7.750 1.2213 0.02494 0.01569 -0.0620 0.2405 1.0000
8.000 1.2438 0.02543 0.01624 -0.0615 0.2377 1.0000
8.250 1.2666 0.02592 0.01673 -0.0611 0.2350 1.0000
8.500 1.2942 0.02649 0.01730 -0.0618 0.2328 1.0000
8.750 1.3357 0.02746 0.01821 -0.0654 0.2299 1.0000
9.000 1.3517 0.02795 0.01885 -0.0636 0.2284 1.0000
9.250 1.3706 0.02855 0.01960 -0.0625 0.2267 1.0000
9.500 1.3892 0.02916 0.02033 -0.0614 0.2248 1.0000
9.750 1.4086 0.02980 0.02107 -0.0604 0.2227 1.0000
10.000 1.4281 0.03042 0.02176 -0.0595 0.2206 1.0000
10.250 1.4496 0.03105 0.02244 -0.0591 0.2184 1.0000
10.500 1.4778 0.03181 0.02320 -0.0600 0.2160 1.0000
10.750 1.5071 0.03300 0.02445 -0.0615 0.2134 1.0000
11.000 1.5151 0.03364 0.02527 -0.0584 0.2120 1.0000
11.250 1.5171 0.03413 0.02594 -0.0542 0.2095 1.0000
11.500 1.5307 0.03499 0.02696 -0.0524 0.2080 1.0000
11.750 1.5371 0.03554 0.02761 -0.0493 0.2052 1.0000
12.000 1.5499 0.03588 0.02796 -0.0474 0.2020 1.0000
12.250 1.5842 0.03686 0.02885 -0.0498 0.1986 1.0000
12.500 1.5822 0.03763 0.02983 -0.0453 0.1968 1.0000
12.750 1.5788 0.03838 0.03078 -0.0407 0.1946 1.0000
13.000 1.5794 0.03919 0.03177 -0.0370 0.1924 1.0000
13.250 1.5814 0.03989 0.03259 -0.0337 0.1898 1.0000
13.500 1.5912 0.04012 0.03280 -0.0316 0.1863 1.0000
13.750 1.6172 0.04079 0.03340 -0.0324 0.1835 1.0000
14.000 1.6131 0.04194 0.03476 -0.0285 0.1816 1.0000
14.250 1.6034 0.04313 0.03618 -0.0240 0.1795 1.0000
14.500 1.5972 0.04437 0.03762 -0.0203 0.1772 1.0000
14.750 1.5950 0.04530 0.03866 -0.0173 0.1743 1.0000
15.000 1.6029 0.04581 0.03918 -0.0156 0.1713 1.0000
15.250 1.6250 0.04619 0.03946 -0.0158 0.1681 1.0000
15.500 1.6067 0.04823 0.04179 -0.0115 0.1664 1.0000
15.750 1.5937 0.05032 0.04412 -0.0083 0.1642 1.0000
16.000 1.5847 0.05222 0.04620 -0.0058 0.1614 1.0000
16.250 1.5837 0.05362 0.04768 -0.0042 0.1584 1.0000
16.500 1.5939 0.05398 0.04789 -0.0035 0.1539 1.0000
16.750 1.5811 0.05692 0.05112 -0.0016 0.1524 1.0000
17.000 1.5613 0.06049 0.05495 0.0000 0.1489 1.0000
17.250 1.5537 0.06328 0.05789 0.0007 0.1461 1.0000
17.500 1.5523 0.06534 0.05992 0.0009 0.1415 1.0000
17.750 1.5322 0.07008 0.06493 0.0008 0.1374 1.0000
18.000 1.5174 0.07456 0.06963 0.0003 0.1342 1.0000
18.250 1.5060 0.07876 0.07384 -0.0008 0.1282 1.0000
18.500 1.4856 0.08456 0.07993 -0.0021 0.1252 1.0000
18.750 1.4577 0.09179 0.08738 -0.0044 0.1199 1.0000
19.000 1.4358 0.09827 0.09391 -0.0067 0.1158 1.0000
19.250 1.3972 0.10757 0.10347 -0.0099 0.1137 1.0000
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Polar data table (+)
Polar graphs
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