Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Glenn Martin 4 (glennmartin4-il) Reynolds number: 200,000 Max Cl/Cd: 54.65 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin4-il-200000.txt Download as CSV file: xf-glennmartin4-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-5.750 -0.2696 0.06271 0.05925 -0.0640 0.9066 0.0675
-5.500 -0.2428 0.05881 0.05520 -0.0661 0.9022 0.0706
-5.250 -0.2402 0.05620 0.05173 -0.0625 0.8892 0.0761
-5.000 -0.2344 0.05013 0.04572 -0.0609 0.8794 0.0773
-4.750 -0.2075 0.04639 0.04195 -0.0617 0.8749 0.0788
-4.500 -0.1938 0.04380 0.03923 -0.0595 0.8639 0.0800
-4.250 -0.1688 0.04078 0.03600 -0.0591 0.8596 0.0839
-4.000 -0.1881 0.03134 0.02484 -0.0460 0.8476 0.0541
-3.750 -0.1613 0.02855 0.02161 -0.0450 0.8440 0.0545
-3.500 -0.1405 0.02729 0.02050 -0.0438 0.8326 0.0575
-3.250 -0.1061 0.02508 0.01797 -0.0441 0.8281 0.0585
-3.000 -0.0810 0.02366 0.01629 -0.0427 0.8158 0.0609
-2.750 -0.0456 0.02241 0.01470 -0.0433 0.8058 0.0637
-2.500 0.0025 0.02042 0.01254 -0.0468 0.7962 0.0666
-2.250 0.0478 0.01927 0.01128 -0.0500 0.7807 0.0706
-2.000 0.0992 0.01834 0.01009 -0.0542 0.7625 0.0762
-1.750 0.1460 0.01699 0.00873 -0.0581 0.7389 0.0840
-1.500 0.1922 0.01607 0.00770 -0.0618 0.7144 0.0980
-1.250 0.2254 0.01557 0.00709 -0.0628 0.6892 0.1150
-1.000 0.2567 0.01538 0.00674 -0.0635 0.6668 0.1323
-0.750 0.2854 0.01526 0.00651 -0.0637 0.6490 0.1459
-0.500 0.3112 0.01518 0.00632 -0.0634 0.6319 0.1620
-0.250 0.3350 0.01509 0.00620 -0.0626 0.6169 0.1854
0.000 0.6551 0.01533 0.00827 -0.1270 0.5749 1.0000
0.250 0.6735 0.01548 0.00823 -0.1254 0.5623 1.0000
0.500 0.6893 0.01561 0.00822 -0.1232 0.5499 1.0000
0.750 0.7048 0.01575 0.00825 -0.1209 0.5377 1.0000
1.000 0.7232 0.01592 0.00827 -0.1192 0.5265 1.0000
1.250 0.7398 0.01610 0.00830 -0.1171 0.5149 1.0000
1.500 0.7550 0.01627 0.00839 -0.1147 0.5033 1.0000
1.750 0.7727 0.01647 0.00846 -0.1129 0.4922 1.0000
2.000 0.7892 0.01667 0.00854 -0.1108 0.4815 1.0000
2.250 0.8050 0.01686 0.00866 -0.1085 0.4707 1.0000
2.500 0.8258 0.01710 0.00876 -0.1074 0.4622 1.0000
2.750 0.8416 0.01728 0.00892 -0.1051 0.4527 1.0000
3.000 0.8632 0.01754 0.00903 -0.1042 0.4453 1.0000
3.250 0.8806 0.01774 0.00923 -0.1023 0.4372 1.0000
3.500 0.9041 0.01802 0.00934 -0.1018 0.4307 1.0000
3.750 0.9220 0.01824 0.00958 -0.1001 0.4237 1.0000
4.000 0.9421 0.01848 0.00976 -0.0989 0.4176 1.0000
4.250 0.9642 0.01876 0.00997 -0.0981 0.4116 1.0000
4.500 0.9836 0.01901 0.01022 -0.0967 0.4059 1.0000
4.750 1.0061 0.01928 0.01042 -0.0961 0.4011 1.0000
5.000 1.0309 0.01961 0.01068 -0.0959 0.3964 1.0000
5.250 1.0501 0.01988 0.01100 -0.0946 0.3917 1.0000
5.500 1.0707 0.02016 0.01125 -0.0935 0.3868 1.0000
5.750 1.0999 0.02051 0.01150 -0.0944 0.3830 1.0000
6.000 1.1199 0.02084 0.01190 -0.0933 0.3793 1.0000
6.250 1.1395 0.02116 0.01226 -0.0921 0.3752 1.0000
6.500 1.1616 0.02149 0.01258 -0.0914 0.3714 1.0000
6.750 1.1897 0.02186 0.01288 -0.0921 0.3673 1.0000
7.000 1.2131 0.02227 0.01335 -0.0918 0.3644 1.0000
7.250 1.2283 0.02263 0.01380 -0.0898 0.3607 1.0000
7.500 1.2484 0.02299 0.01422 -0.0889 0.3572 1.0000
7.750 1.2715 0.02335 0.01456 -0.0885 0.3536 1.0000
8.000 1.3040 0.02386 0.01501 -0.0903 0.3499 1.0000
8.250 1.3138 0.02426 0.01557 -0.0872 0.3468 1.0000
8.500 1.3299 0.02469 0.01611 -0.0855 0.3437 1.0000
8.750 1.3476 0.02507 0.01654 -0.0841 0.3399 1.0000
9.000 1.3739 0.02546 0.01687 -0.0846 0.3357 1.0000
9.250 1.3777 0.02587 0.01740 -0.0805 0.3309 1.0000
9.500 1.3841 0.02626 0.01790 -0.0770 0.3265 1.0000
9.750 1.3968 0.02653 0.01816 -0.0747 0.3213 1.0000
10.000 1.4051 0.02698 0.01865 -0.0717 0.3158 1.0000
10.250 1.4092 0.02746 0.01927 -0.0679 0.3118 1.0000
10.500 1.4167 0.02782 0.01968 -0.0649 0.3067 1.0000
10.750 1.4296 0.02826 0.02009 -0.0630 0.3013 1.0000
11.000 1.4242 0.02889 0.02093 -0.0577 0.2962 1.0000
11.250 1.4249 0.02939 0.02149 -0.0538 0.2903 1.0000
11.500 1.4259 0.03004 0.02218 -0.0500 0.2841 1.0000
11.750 1.4254 0.03084 0.02314 -0.0462 0.2787 1.0000
12.000 1.4263 0.03160 0.02389 -0.0429 0.2721 1.0000
12.250 1.4219 0.03272 0.02521 -0.0390 0.2648 1.0000
12.500 1.4145 0.03404 0.02658 -0.0349 0.2546 1.0000
12.750 1.4111 0.03547 0.02815 -0.0318 0.2440 1.0000
13.000 1.4010 0.03750 0.03020 -0.0283 0.2273 1.0000
13.250 1.3842 0.04037 0.03301 -0.0248 0.1990 1.0000
13.500 1.3601 0.04418 0.03667 -0.0214 0.1682 1.0000
13.750 1.3308 0.04890 0.04126 -0.0185 0.1414 1.0000
14.000 1.3083 0.05338 0.04570 -0.0167 0.1224 1.0000
14.250 1.2795 0.05885 0.05112 -0.0154 0.1001 1.0000
14.500 1.2483 0.06495 0.05720 -0.0146 0.0667 1.0000
14.750 1.2195 0.07106 0.06334 -0.0144 0.0577 1.0000
15.000 1.1949 0.07690 0.06925 -0.0145 0.0526 1.0000
15.250 1.1744 0.08240 0.07488 -0.0147 0.0484 1.0000
15.500 1.1575 0.08757 0.08019 -0.0152 0.0461 1.0000
15.750 1.1409 0.09283 0.08559 -0.0158 0.0445 1.0000
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Polar data table (+)
Polar graphs
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