Glenn Martin 3 (glennmartin3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Glenn Martin 3 (glennmartin3-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.74 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin3-il-1000000.txt Download as CSV file: xf-glennmartin3-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7459 0.04494 0.04257 -0.1086 0.9785 0.0156
-13.250 -0.8169 0.03695 0.03408 -0.1041 0.9709 0.0154
-13.000 -0.8283 0.03387 0.03070 -0.1007 0.9683 0.0154
-12.750 -0.8012 0.03374 0.03051 -0.1007 0.9676 0.0157
-12.500 -0.8092 0.03227 0.02887 -0.0952 0.9618 0.0158
-12.250 -0.8242 0.02938 0.02567 -0.0895 0.9581 0.0162
-12.000 -0.8021 0.02897 0.02525 -0.0886 0.9571 0.0165
-11.750 -0.8009 0.02787 0.02404 -0.0838 0.9517 0.0166
-11.500 -0.7779 0.02774 0.02393 -0.0827 0.9493 0.0168
-11.250 -0.7561 0.02713 0.02326 -0.0817 0.9478 0.0170
-11.000 -0.7312 0.02668 0.02276 -0.0812 0.9467 0.0174
-10.750 -0.7089 0.02582 0.02178 -0.0803 0.9458 0.0178
-10.500 -0.7050 0.02499 0.02084 -0.0756 0.9398 0.0180
-10.250 -0.6879 0.02400 0.01969 -0.0735 0.9371 0.0185
-10.000 -0.6673 0.02300 0.01853 -0.0721 0.9356 0.0188
-9.750 -0.6413 0.02255 0.01797 -0.0716 0.9346 0.0190
-9.500 -0.6234 0.02075 0.01600 -0.0700 0.9337 0.0196
-9.250 -0.6144 0.02070 0.01598 -0.0658 0.9269 0.0200
-9.000 -0.5900 0.02037 0.01563 -0.0650 0.9248 0.0202
-8.750 -0.5625 0.01994 0.01516 -0.0646 0.9234 0.0207
-8.500 -0.5360 0.01918 0.01430 -0.0642 0.9223 0.0211
-8.250 -0.5080 0.01861 0.01364 -0.0640 0.9214 0.0218
-8.000 -0.4785 0.01788 0.01281 -0.0641 0.9205 0.0222
-7.750 -0.4708 0.01774 0.01258 -0.0594 0.9128 0.0226
-7.500 -0.4471 0.01653 0.01126 -0.0585 0.9110 0.0231
-7.250 -0.4197 0.01595 0.01067 -0.0582 0.9097 0.0237
-7.000 -0.3904 0.01560 0.01032 -0.0583 0.9084 0.0243
-6.750 -0.3591 0.01502 0.00968 -0.0588 0.9072 0.0247
-6.500 -0.3425 0.01475 0.00937 -0.0560 0.9007 0.0255
-6.250 -0.3150 0.01425 0.00880 -0.0557 0.8975 0.0260
-6.000 -0.2838 0.01407 0.00855 -0.0560 0.8950 0.0267
-5.750 -0.2469 0.01292 0.00734 -0.0580 0.8936 0.0275
-5.500 -0.2098 0.01243 0.00687 -0.0598 0.8924 0.0283
-5.250 -0.1924 0.01229 0.00671 -0.0573 0.8849 0.0291
-5.000 -0.1577 0.01190 0.00629 -0.0586 0.8815 0.0299
-4.750 -0.1133 0.01142 0.00576 -0.0620 0.8777 0.0309
-4.500 -0.0892 0.01123 0.00554 -0.0610 0.8702 0.0313
-4.250 -0.0513 0.01059 0.00486 -0.0631 0.8644 0.0324
-4.000 -0.0185 0.01024 0.00448 -0.0640 0.8554 0.0332
-3.750 0.0179 0.00996 0.00417 -0.0658 0.8472 0.0342
-3.500 0.0471 0.00978 0.00396 -0.0659 0.8390 0.0353
-3.250 0.0842 0.00958 0.00370 -0.0678 0.8291 0.0364
-3.000 0.1072 0.00945 0.00353 -0.0665 0.8200 0.0367
-2.750 0.1398 0.00914 0.00317 -0.0675 0.8084 0.0389
-2.500 0.1627 0.00905 0.00305 -0.0662 0.7984 0.0398
-2.250 0.1855 0.00896 0.00293 -0.0649 0.7878 0.0412
-2.000 0.2081 0.00891 0.00283 -0.0636 0.7762 0.0424
-1.750 0.2250 0.00888 0.00273 -0.0610 0.7588 0.0444
-1.500 0.2413 0.00885 0.00267 -0.0583 0.7366 0.0486
-1.250 0.2516 0.00893 0.00262 -0.0542 0.7001 0.0524
-1.000 0.2568 0.00914 0.00265 -0.0490 0.6534 0.0591
-0.750 0.2672 0.00929 0.00268 -0.0451 0.6115 0.0811
-0.500 0.2823 0.00933 0.00278 -0.0425 0.5722 0.1517
-0.250 0.2927 0.00962 0.00289 -0.0388 0.5157 0.1686
0.000 0.3049 0.00994 0.00301 -0.0355 0.4615 0.1827
0.250 0.3235 0.01012 0.00310 -0.0336 0.4331 0.2029
0.500 0.3475 0.01011 0.00317 -0.0330 0.4159 0.2543
0.750 0.5685 0.01064 0.00558 -0.0776 0.3763 0.9764
1.000 0.6283 0.01114 0.00595 -0.0849 0.3593 0.9841
1.250 0.6961 0.01120 0.00586 -0.0940 0.3381 0.9894
1.500 0.7296 0.01135 0.00591 -0.0955 0.3226 0.9923
1.750 0.7723 0.01143 0.00584 -0.0991 0.3007 0.9959
2.000 0.8165 0.01139 0.00564 -0.1031 0.2780 0.9993
2.250 0.8407 0.01152 0.00566 -0.1026 0.2617 1.0000
2.500 0.8582 0.01168 0.00576 -0.1006 0.2513 1.0000
2.750 0.8761 0.01186 0.00587 -0.0988 0.2420 1.0000
3.000 0.8942 0.01203 0.00599 -0.0969 0.2343 1.0000
3.250 0.9128 0.01221 0.00612 -0.0952 0.2269 1.0000
3.500 0.9321 0.01237 0.00625 -0.0936 0.2227 1.0000
3.750 0.9507 0.01257 0.00640 -0.0919 0.2167 1.0000
4.000 0.9699 0.01274 0.00656 -0.0903 0.2129 1.0000
4.250 0.9897 0.01289 0.00670 -0.0889 0.2100 1.0000
4.500 1.0085 0.01307 0.00686 -0.0872 0.2069 1.0000
4.750 1.0270 0.01329 0.00705 -0.0856 0.2033 1.0000
5.000 1.0442 0.01356 0.00729 -0.0837 0.1983 1.0000
5.250 1.0642 0.01371 0.00745 -0.0823 0.1974 1.0000
5.500 1.0843 0.01387 0.00763 -0.0810 0.1954 1.0000
5.750 1.1039 0.01406 0.00781 -0.0796 0.1933 1.0000
6.000 1.1231 0.01427 0.00802 -0.0782 0.1911 1.0000
6.250 1.1417 0.01450 0.00825 -0.0767 0.1891 1.0000
6.500 1.1591 0.01479 0.00852 -0.0750 0.1863 1.0000
6.750 1.1753 0.01513 0.00887 -0.0731 0.1832 1.0000
7.000 1.1948 0.01534 0.00909 -0.0718 0.1823 1.0000
7.250 1.2143 0.01555 0.00933 -0.0705 0.1812 1.0000
7.500 1.2341 0.01575 0.00957 -0.0693 0.1801 1.0000
7.750 1.2524 0.01602 0.00986 -0.0679 0.1791 1.0000
8.000 1.2708 0.01628 0.01013 -0.0665 0.1775 1.0000
8.250 1.2889 0.01656 0.01044 -0.0650 0.1761 1.0000
8.500 1.3067 0.01686 0.01075 -0.0636 0.1748 1.0000
8.750 1.3239 0.01720 0.01108 -0.0621 0.1713 1.0000
9.000 1.3393 0.01761 0.01150 -0.0603 0.1697 1.0000
9.250 1.3562 0.01795 0.01187 -0.0588 0.1674 1.0000
9.500 1.3756 0.01817 0.01214 -0.0578 0.1664 1.0000
9.750 1.3938 0.01847 0.01247 -0.0565 0.1652 1.0000
10.000 1.4131 0.01871 0.01273 -0.0555 0.1628 1.0000
10.250 1.4286 0.01913 0.01320 -0.0539 0.1625 1.0000
10.500 1.4460 0.01947 0.01355 -0.0526 0.1603 1.0000
10.750 1.4621 0.01987 0.01398 -0.0512 0.1589 1.0000
11.000 1.4754 0.02041 0.01452 -0.0493 0.1556 1.0000
11.250 1.4895 0.02093 0.01507 -0.0476 0.1539 1.0000
11.500 1.5073 0.02126 0.01546 -0.0465 0.1531 1.0000
11.750 1.5246 0.02162 0.01587 -0.0454 0.1519 1.0000
12.000 1.5425 0.02194 0.01625 -0.0445 0.1494 1.0000
12.250 1.5582 0.02240 0.01674 -0.0432 0.1478 1.0000
12.500 1.5735 0.02288 0.01724 -0.0419 0.1449 1.0000
12.750 1.5855 0.02356 0.01792 -0.0402 0.1417 1.0000
13.000 1.6010 0.02406 0.01847 -0.0390 0.1398 1.0000
13.250 1.6180 0.02446 0.01893 -0.0381 0.1371 1.0000
13.500 1.6324 0.02502 0.01950 -0.0369 0.1324 1.0000
13.750 1.6438 0.02579 0.02026 -0.0353 0.1280 1.0000
14.000 1.6582 0.02637 0.02091 -0.0342 0.1250 1.0000
14.250 1.6690 0.02720 0.02172 -0.0326 0.1181 1.0000
14.500 1.6737 0.02845 0.02290 -0.0304 0.1045 1.0000
14.750 1.6607 0.03094 0.02520 -0.0264 0.0794 1.0000
15.000 1.6390 0.03420 0.02831 -0.0219 0.0561 1.0000
15.250 1.6241 0.03717 0.03122 -0.0184 0.0412 1.0000
15.500 1.5986 0.04122 0.03522 -0.0147 0.0254 1.0000
15.750 1.5894 0.04412 0.03817 -0.0127 0.0210 1.0000
16.000 1.5832 0.04692 0.04104 -0.0112 0.0189 1.0000
16.250 1.5767 0.04989 0.04410 -0.0101 0.0175 1.0000
16.500 1.5615 0.05396 0.04826 -0.0090 0.0154 1.0000
16.750 1.5570 0.05703 0.05142 -0.0086 0.0147 1.0000
17.000 1.5499 0.06056 0.05506 -0.0084 0.0147 1.0000
17.250 1.5420 0.06430 0.05892 -0.0085 0.0146 1.0000
17.500 1.5287 0.06891 0.06366 -0.0089 0.0144 1.0000
17.750 1.5111 0.07427 0.06916 -0.0098 0.0138 1.0000
18.000 1.4945 0.07973 0.07476 -0.0110 0.0139 1.0000
18.250 1.4694 0.08663 0.08180 -0.0127 0.0134 1.0000
18.500 1.4460 0.09333 0.08864 -0.0145 0.0133 1.0000
18.750 1.4137 0.10150 0.09698 -0.0168 0.0133 1.0000
19.000 1.3907 0.10831 0.10394 -0.0189 0.0135 1.0000
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Polar data table (+)
Polar graphs
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