Glenn Martin 4 (glennmartin4-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Glenn Martin 4 (glennmartin4-il) Reynolds number: 500,000 Max Cl/Cd: 62.85 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-glennmartin4-il-500000-n5.txt Download as CSV file: xf-glennmartin4-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6085 0.04183 0.03881 -0.1010 0.9418 0.0103
-10.750 -0.6569 0.03417 0.03051 -0.0926 0.9329 0.0101
-10.500 -0.6403 0.03228 0.02842 -0.0918 0.9314 0.0104
-10.250 -0.6381 0.03138 0.02746 -0.0871 0.9242 0.0107
-10.000 -0.6242 0.02958 0.02544 -0.0854 0.9217 0.0108
-9.750 -0.6030 0.02819 0.02387 -0.0848 0.9200 0.0112
-9.500 -0.6024 0.02689 0.02237 -0.0798 0.9122 0.0114
-9.250 -0.5847 0.02551 0.02075 -0.0782 0.9094 0.0121
-9.000 -0.5644 0.02417 0.01918 -0.0770 0.9075 0.0123
-8.750 -0.5560 0.02329 0.01816 -0.0732 0.9004 0.0125
-8.500 -0.5372 0.02237 0.01714 -0.0715 0.8962 0.0129
-8.250 -0.5101 0.02187 0.01660 -0.0713 0.8937 0.0135
-8.000 -0.4942 0.02131 0.01596 -0.0688 0.8874 0.0139
-7.750 -0.4768 0.02063 0.01516 -0.0666 0.8818 0.0142
-7.500 -0.4543 0.01986 0.01426 -0.0654 0.8783 0.0147
-7.250 -0.4331 0.01949 0.01378 -0.0639 0.8728 0.0156
-7.000 -0.4153 0.01880 0.01298 -0.0617 0.8653 0.0160
-6.750 -0.3879 0.01818 0.01230 -0.0614 0.8613 0.0166
-6.500 -0.3633 0.01785 0.01194 -0.0606 0.8520 0.0174
-6.250 -0.3272 0.01718 0.01117 -0.0620 0.8444 0.0185
-6.000 -0.2922 0.01659 0.01042 -0.0633 0.8342 0.0196
-5.750 -0.2428 0.01556 0.00926 -0.0677 0.8198 0.0205
-5.500 -0.1890 0.01496 0.00852 -0.0731 0.7978 0.0222
-5.250 -0.1489 0.01457 0.00792 -0.0756 0.7718 0.0238
-5.000 -0.1225 0.01435 0.00744 -0.0751 0.7305 0.0245
-4.750 -0.1083 0.01424 0.00710 -0.0721 0.6875 0.0255
-4.500 -0.0978 0.01416 0.00682 -0.0684 0.6506 0.0264
-4.250 -0.0837 0.01415 0.00665 -0.0654 0.6248 0.0272
-4.000 -0.0676 0.01406 0.00642 -0.0629 0.6045 0.0281
-3.750 -0.0493 0.01400 0.00624 -0.0608 0.5895 0.0290
-3.500 -0.0311 0.01392 0.00605 -0.0587 0.5743 0.0301
-3.000 0.0079 0.01371 0.00566 -0.0551 0.5519 0.0317
-2.750 0.0274 0.01357 0.00545 -0.0533 0.5424 0.0336
-2.500 0.0488 0.01347 0.00530 -0.0520 0.5340 0.0348
-2.250 0.0697 0.01342 0.00517 -0.0505 0.5258 0.0362
-2.000 0.0916 0.01336 0.00504 -0.0492 0.5161 0.0373
-1.750 0.1132 0.01333 0.00495 -0.0480 0.5089 0.0391
-1.500 0.1362 0.01326 0.00487 -0.0470 0.5004 0.0429
-1.250 0.1585 0.01325 0.00488 -0.0459 0.4929 0.0502
-1.000 0.1819 0.01326 0.00489 -0.0451 0.4852 0.0588
-0.750 0.2043 0.01332 0.00490 -0.0440 0.4769 0.0654
-0.500 0.2280 0.01334 0.00488 -0.0432 0.4696 0.0692
-0.250 0.2506 0.01342 0.00489 -0.0422 0.4609 0.0733
0.000 0.2743 0.01344 0.00487 -0.0415 0.4528 0.0762
0.250 0.2971 0.01348 0.00487 -0.0407 0.4430 0.0813
0.500 0.3208 0.01353 0.00487 -0.0399 0.4331 0.0832
0.750 0.3435 0.01362 0.00488 -0.0391 0.4240 0.0853
1.000 0.3652 0.01374 0.00493 -0.0381 0.4097 0.0867
1.250 0.3900 0.01379 0.00496 -0.0377 0.4015 0.0899
1.500 0.4131 0.01391 0.00503 -0.0370 0.3907 0.0935
2.000 0.4633 0.01406 0.00522 -0.0366 0.3729 0.1274
2.250 0.4877 0.01419 0.00532 -0.0363 0.3647 0.1437
2.750 0.7751 0.01429 0.00749 -0.0909 0.3392 0.9957
3.000 0.8194 0.01463 0.00775 -0.0951 0.3330 0.9995
3.250 0.8435 0.01486 0.00792 -0.0947 0.3286 1.0000
3.500 0.8642 0.01501 0.00804 -0.0936 0.3257 1.0000
3.750 0.8844 0.01518 0.00819 -0.0924 0.3222 1.0000
4.000 0.9045 0.01536 0.00835 -0.0912 0.3188 1.0000
4.250 0.9241 0.01557 0.00852 -0.0899 0.3159 1.0000
4.500 0.9436 0.01580 0.00871 -0.0886 0.3131 1.0000
4.750 0.9638 0.01598 0.00889 -0.0875 0.3100 1.0000
5.000 0.9840 0.01617 0.00909 -0.0863 0.3085 1.0000
5.250 1.0037 0.01638 0.00930 -0.0851 0.3053 1.0000
5.500 1.0231 0.01661 0.00953 -0.0839 0.3025 1.0000
5.750 1.0423 0.01685 0.00976 -0.0827 0.3005 1.0000
6.000 1.0610 0.01712 0.01002 -0.0813 0.2982 1.0000
6.250 1.0797 0.01740 0.01029 -0.0801 0.2957 1.0000
6.500 1.0998 0.01762 0.01054 -0.0790 0.2940 1.0000
6.750 1.1196 0.01785 0.01079 -0.0780 0.2909 1.0000
7.000 1.1385 0.01812 0.01109 -0.0768 0.2891 1.0000
7.250 1.1570 0.01841 0.01139 -0.0755 0.2870 1.0000
7.500 1.1754 0.01871 0.01171 -0.0743 0.2850 1.0000
7.750 1.1933 0.01903 0.01205 -0.0730 0.2828 1.0000
8.000 1.2095 0.01942 0.01244 -0.0715 0.2797 1.0000
8.250 1.2288 0.01969 0.01277 -0.0705 0.2773 1.0000
8.500 1.2470 0.01999 0.01311 -0.0693 0.2735 1.0000
8.750 1.2626 0.02041 0.01351 -0.0678 0.2671 1.0000
9.000 1.2790 0.02080 0.01392 -0.0664 0.2627 1.0000
9.250 1.2966 0.02116 0.01434 -0.0652 0.2600 1.0000
9.500 1.3134 0.02155 0.01477 -0.0639 0.2564 1.0000
9.750 1.3257 0.02216 0.01534 -0.0620 0.2488 1.0000
10.000 1.3416 0.02261 0.01581 -0.0607 0.2400 1.0000
10.250 1.3551 0.02318 0.01640 -0.0590 0.2357 1.0000
10.500 1.3671 0.02384 0.01706 -0.0572 0.2229 1.0000
10.750 1.3730 0.02485 0.01797 -0.0546 0.2055 1.0000
11.000 1.3831 0.02565 0.01878 -0.0526 0.1948 1.0000
11.250 1.3733 0.02764 0.02055 -0.0481 0.1623 1.0000
11.500 1.3718 0.02923 0.02207 -0.0450 0.1447 1.0000
11.750 1.3609 0.03150 0.02423 -0.0409 0.1208 1.0000
12.000 1.3323 0.03520 0.02773 -0.0354 0.0766 1.0000
12.250 1.3162 0.03829 0.03078 -0.0318 0.0529 1.0000
12.500 1.3015 0.04148 0.03402 -0.0289 0.0333 1.0000
12.750 1.2930 0.04438 0.03694 -0.0269 0.0219 1.0000
13.000 1.2882 0.04710 0.03971 -0.0255 0.0171 1.0000
13.250 1.2897 0.04931 0.04203 -0.0246 0.0171 1.0000
13.500 1.2858 0.05216 0.04497 -0.0237 0.0156 1.0000
13.750 1.2820 0.05510 0.04801 -0.0230 0.0147 1.0000
14.000 1.2754 0.05841 0.05142 -0.0224 0.0137 1.0000
14.250 1.2728 0.06136 0.05447 -0.0221 0.0132 1.0000
14.500 1.2675 0.06467 0.05789 -0.0218 0.0127 1.0000
14.750 1.2589 0.06843 0.06177 -0.0216 0.0119 1.0000
15.000 1.2510 0.07216 0.06561 -0.0215 0.0119 1.0000
15.250 1.2416 0.07613 0.06969 -0.0215 0.0116 1.0000
15.500 1.2305 0.08037 0.07404 -0.0217 0.0112 1.0000
15.750 1.2169 0.08503 0.07881 -0.0220 0.0107 1.0000
16.000 1.2072 0.08923 0.08312 -0.0224 0.0109 1.0000
16.250 1.1932 0.09408 0.08808 -0.0230 0.0101 1.0000
16.500 1.1827 0.09853 0.09263 -0.0236 0.0101 1.0000
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Polar data table (+)
Polar graphs
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