Glenn Martin 3 (glennmartin3-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Glenn Martin 3 (glennmartin3-il) Reynolds number: 500,000 Max Cl/Cd: 62.62 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-glennmartin3-il-500000-n5.txt Download as CSV file: xf-glennmartin3-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6591 0.04266 0.03960 -0.1107 0.9622 0.0143
-12.250 -0.5942 0.04758 0.04482 -0.1107 0.9627 0.0146
-12.000 -0.7216 0.03448 0.03069 -0.0988 0.9508 0.0146
-11.750 -0.7054 0.03379 0.02991 -0.0972 0.9491 0.0152
-11.500 -0.7248 0.03165 0.02751 -0.0896 0.9415 0.0153
-11.250 -0.7211 0.02948 0.02502 -0.0862 0.9384 0.0157
-10.750 -0.7142 0.02644 0.02152 -0.0778 0.9286 0.0164
-10.500 -0.6921 0.02600 0.02106 -0.0767 0.9266 0.0167
-10.250 -0.6677 0.02563 0.02065 -0.0759 0.9252 0.0170
-10.000 -0.6567 0.02502 0.01995 -0.0726 0.9204 0.0172
-9.750 -0.6397 0.02473 0.01962 -0.0702 0.9162 0.0177
-9.500 -0.6219 0.02371 0.01844 -0.0683 0.9138 0.0180
-9.250 -0.5994 0.02300 0.01759 -0.0672 0.9122 0.0187
-9.000 -0.5788 0.02174 0.01605 -0.0657 0.9109 0.0195
-8.750 -0.5680 0.02141 0.01565 -0.0621 0.9049 0.0198
-8.500 -0.5487 0.02085 0.01504 -0.0602 0.9015 0.0201
-8.250 -0.5249 0.02055 0.01472 -0.0592 0.8995 0.0206
-8.000 -0.5011 0.01989 0.01397 -0.0581 0.8980 0.0209
-7.750 -0.4722 0.01949 0.01351 -0.0581 0.8962 0.0217
-7.500 -0.4567 0.01897 0.01286 -0.0553 0.8910 0.0222
-7.250 -0.4351 0.01847 0.01222 -0.0536 0.8860 0.0231
-7.000 -0.4083 0.01778 0.01140 -0.0532 0.8833 0.0236
-6.750 -0.3782 0.01724 0.01084 -0.0535 0.8812 0.0241
-6.500 -0.3446 0.01665 0.01022 -0.0545 0.8794 0.0248
-6.250 -0.3304 0.01642 0.00994 -0.0513 0.8714 0.0253
-6.000 -0.3003 0.01592 0.00937 -0.0515 0.8680 0.0260
-5.750 -0.2676 0.01549 0.00886 -0.0523 0.8658 0.0271
-5.500 -0.2318 0.01500 0.00827 -0.0538 0.8637 0.0277
-5.250 -0.2056 0.01449 0.00772 -0.0533 0.8589 0.0281
-5.000 -0.1787 0.01411 0.00733 -0.0529 0.8535 0.0290
-4.750 -0.1455 0.01375 0.00696 -0.0539 0.8499 0.0300
-4.500 -0.1082 0.01329 0.00646 -0.0558 0.8470 0.0308
-4.250 -0.0764 0.01297 0.00611 -0.0565 0.8430 0.0316
-4.000 -0.0504 0.01269 0.00578 -0.0559 0.8357 0.0321
-3.750 -0.0062 0.01226 0.00527 -0.0593 0.8283 0.0333
-3.500 0.0181 0.01199 0.00500 -0.0583 0.8194 0.0343
-3.250 0.0561 0.01169 0.00463 -0.0604 0.8083 0.0351
-3.000 0.0832 0.01150 0.00439 -0.0601 0.7944 0.0359
-2.750 0.1083 0.01137 0.00419 -0.0593 0.7765 0.0368
-2.500 0.1319 0.01126 0.00400 -0.0582 0.7587 0.0383
-2.250 0.1542 0.01116 0.00383 -0.0568 0.7388 0.0397
-2.000 0.1722 0.01113 0.00368 -0.0544 0.7036 0.0413
-1.750 0.1826 0.01127 0.00360 -0.0504 0.6589 0.0425
-1.500 0.1885 0.01154 0.00362 -0.0455 0.6120 0.0438
-1.250 0.2023 0.01170 0.00363 -0.0424 0.5777 0.0467
-1.000 0.2164 0.01188 0.00367 -0.0394 0.5409 0.0490
-0.750 0.2250 0.01219 0.00376 -0.0354 0.4828 0.0592
-0.500 0.2411 0.01239 0.00382 -0.0329 0.4495 0.0699
-0.250 0.2646 0.01236 0.00387 -0.0323 0.4278 0.1206
0.250 0.3085 0.01252 0.00400 -0.0300 0.4004 0.1651
0.500 0.3310 0.01259 0.00406 -0.0290 0.3895 0.1808
0.750 0.3548 0.01262 0.00412 -0.0283 0.3797 0.2031
1.000 0.3927 0.01200 0.00426 -0.0313 0.3672 0.4646
1.250 0.6295 0.01325 0.00662 -0.0788 0.3191 0.9832
1.500 0.6656 0.01354 0.00677 -0.0809 0.3010 0.9869
1.750 0.7130 0.01374 0.00683 -0.0856 0.2832 0.9921
2.000 0.7583 0.01387 0.00682 -0.0898 0.2656 0.9967
2.250 0.7969 0.01394 0.00677 -0.0926 0.2530 0.9996
2.500 0.8184 0.01412 0.00688 -0.0916 0.2441 1.0000
2.750 0.8365 0.01433 0.00702 -0.0898 0.2369 1.0000
3.000 0.8548 0.01454 0.00718 -0.0880 0.2296 1.0000
3.250 0.8732 0.01475 0.00734 -0.0863 0.2249 1.0000
3.500 0.8922 0.01494 0.00750 -0.0847 0.2205 1.0000
3.750 0.9113 0.01514 0.00767 -0.0831 0.2161 1.0000
4.000 0.9301 0.01535 0.00786 -0.0816 0.2124 1.0000
4.250 0.9484 0.01560 0.00807 -0.0799 0.2085 1.0000
4.500 0.9674 0.01582 0.00828 -0.0784 0.2057 1.0000
4.750 0.9865 0.01603 0.00849 -0.0769 0.2034 1.0000
5.000 1.0053 0.01625 0.00871 -0.0754 0.2005 1.0000
5.250 1.0240 0.01650 0.00894 -0.0739 0.1980 1.0000
5.500 1.0422 0.01678 0.00920 -0.0723 0.1950 1.0000
5.750 1.0604 0.01706 0.00948 -0.0708 0.1925 1.0000
6.000 1.0785 0.01735 0.00976 -0.0692 0.1909 1.0000
6.250 1.0975 0.01759 0.01003 -0.0678 0.1892 1.0000
6.500 1.1161 0.01785 0.01032 -0.0664 0.1879 1.0000
6.750 1.1347 0.01812 0.01060 -0.0651 0.1855 1.0000
7.000 1.1531 0.01842 0.01091 -0.0637 0.1837 1.0000
7.250 1.1708 0.01874 0.01124 -0.0622 0.1818 1.0000
7.500 1.1881 0.01908 0.01160 -0.0606 0.1803 1.0000
7.750 1.2051 0.01944 0.01197 -0.0591 0.1787 1.0000
8.000 1.2218 0.01983 0.01238 -0.0575 0.1772 1.0000
8.250 1.2379 0.02026 0.01282 -0.0559 0.1755 1.0000
8.500 1.2558 0.02059 0.01320 -0.0546 0.1745 1.0000
8.750 1.2731 0.02095 0.01360 -0.0532 0.1736 1.0000
9.000 1.2903 0.02133 0.01404 -0.0518 0.1728 1.0000
9.250 1.3075 0.02172 0.01448 -0.0505 0.1716 1.0000
9.500 1.3239 0.02215 0.01495 -0.0491 0.1706 1.0000
9.750 1.3402 0.02258 0.01544 -0.0477 0.1694 1.0000
10.000 1.3566 0.02302 0.01593 -0.0463 0.1685 1.0000
10.250 1.3721 0.02352 0.01646 -0.0449 0.1672 1.0000
10.500 1.3873 0.02403 0.01701 -0.0434 0.1658 1.0000
10.750 1.4011 0.02461 0.01758 -0.0419 0.1624 1.0000
11.000 1.4153 0.02519 0.01820 -0.0404 0.1600 1.0000
11.250 1.4310 0.02569 0.01878 -0.0391 0.1591 1.0000
11.500 1.4479 0.02612 0.01927 -0.0381 0.1557 1.0000
11.750 1.4627 0.02668 0.01989 -0.0369 0.1538 1.0000
12.000 1.4768 0.02729 0.02056 -0.0355 0.1519 1.0000
12.250 1.4894 0.02800 0.02128 -0.0341 0.1490 1.0000
12.500 1.5008 0.02880 0.02210 -0.0325 0.1461 1.0000
12.750 1.5157 0.02940 0.02280 -0.0315 0.1448 1.0000
13.000 1.5296 0.03008 0.02356 -0.0303 0.1431 1.0000
13.250 1.5430 0.03079 0.02435 -0.0291 0.1412 1.0000
13.500 1.5546 0.03163 0.02523 -0.0278 0.1374 1.0000
13.750 1.5649 0.03257 0.02621 -0.0265 0.1349 1.0000
14.000 1.5764 0.03345 0.02716 -0.0253 0.1317 1.0000
14.250 1.5866 0.03445 0.02817 -0.0241 0.1234 1.0000
14.750 1.6029 0.03680 0.03061 -0.0214 0.1130 1.0000
15.000 1.6072 0.03833 0.03214 -0.0199 0.1044 1.0000
15.250 1.5921 0.04153 0.03518 -0.0170 0.0823 1.0000
15.500 1.5866 0.04403 0.03770 -0.0152 0.0737 1.0000
15.750 1.5787 0.04689 0.04059 -0.0135 0.0649 1.0000
16.000 1.5328 0.05382 0.04741 -0.0107 0.0387 1.0000
16.250 1.5248 0.05719 0.05086 -0.0100 0.0347 1.0000
16.500 1.5014 0.06261 0.05636 -0.0095 0.0270 1.0000
16.750 1.4770 0.06849 0.06234 -0.0097 0.0218 1.0000
17.000 1.4527 0.07474 0.06872 -0.0105 0.0189 1.0000
17.250 1.4375 0.07999 0.07412 -0.0115 0.0184 1.0000
17.500 1.4180 0.08607 0.08034 -0.0130 0.0177 1.0000
17.750 1.3911 0.09336 0.08778 -0.0149 0.0165 1.0000
18.000 1.3715 0.09959 0.09417 -0.0166 0.0168 1.0000
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Polar data table (+)
Polar graphs
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