Glenn Martin 3 (glennmartin3-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Glenn Martin 3 (glennmartin3-il) Reynolds number: 500,000 Max Cl/Cd: 62.83 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-glennmartin3-il-500000.txt Download as CSV file: xf-glennmartin3-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3403 0.07315 0.07083 -0.0852 0.9607 0.0314
-9.250 -0.3521 0.06783 0.06545 -0.0868 0.9575 0.0317
-9.000 -0.3451 0.06675 0.06436 -0.0857 0.9546 0.0319
-7.750 -0.4424 0.03912 0.03524 -0.0644 0.9216 0.0319
-7.500 -0.4263 0.03715 0.03323 -0.0629 0.9186 0.0322
-7.250 -0.4292 0.03440 0.03032 -0.0573 0.9112 0.0296
-7.000 -0.4282 0.02973 0.02504 -0.0523 0.9082 0.0297
-6.750 -0.4129 0.02727 0.02216 -0.0496 0.9069 0.0306
-6.500 -0.4205 0.02590 0.02051 -0.0421 0.8980 0.0307
-6.250 -0.4018 0.02486 0.01909 -0.0397 0.8957 0.0314
-6.000 -0.3779 0.02249 0.01653 -0.0389 0.8946 0.0324
-5.750 -0.3462 0.02144 0.01539 -0.0395 0.8936 0.0330
-5.500 -0.3135 0.02055 0.01443 -0.0402 0.8929 0.0339
-5.250 -0.3077 0.02040 0.01421 -0.0354 0.8854 0.0350
-5.000 -0.2801 0.01954 0.01320 -0.0349 0.8833 0.0357
-4.750 -0.2502 0.01895 0.01243 -0.0348 0.8817 0.0367
-4.500 -0.2097 0.01746 0.01090 -0.0373 0.8811 0.0379
-4.250 -0.1713 0.01666 0.01010 -0.0393 0.8801 0.0391
-4.000 -0.1340 0.01599 0.00942 -0.0410 0.8792 0.0405
-3.750 -0.0899 0.01513 0.00852 -0.0441 0.8783 0.0416
-3.500 -0.0449 0.01445 0.00779 -0.0474 0.8771 0.0428
-3.250 -0.0273 0.01383 0.00716 -0.0449 0.8679 0.0442
-3.000 0.0178 0.01306 0.00641 -0.0483 0.8642 0.0455
-2.750 0.0722 0.01231 0.00565 -0.0538 0.8610 0.0482
-2.500 0.0894 0.01210 0.00541 -0.0511 0.8499 0.0491
-2.250 0.1459 0.01140 0.00470 -0.0572 0.8451 0.0523
-2.000 0.1666 0.01123 0.00453 -0.0554 0.8345 0.0546
-1.750 0.2185 0.01083 0.00409 -0.0606 0.8276 0.0594
-1.500 0.2408 0.01063 0.00392 -0.0592 0.8168 0.0677
-1.250 0.2798 0.01003 0.00365 -0.0618 0.8049 0.1602
-0.750 0.3395 0.00956 0.00340 -0.0626 0.7763 0.2605
-0.500 0.3630 0.00892 0.00341 -0.0620 0.7575 0.4791
0.500 0.6944 0.01189 0.00599 -0.1109 0.4383 1.0000
0.750 0.7084 0.01209 0.00606 -0.1082 0.4204 1.0000
1.000 0.7243 0.01225 0.00612 -0.1059 0.4064 1.0000
1.250 0.7404 0.01241 0.00620 -0.1036 0.3939 1.0000
1.500 0.7561 0.01260 0.00629 -0.1013 0.3800 1.0000
1.750 0.7732 0.01275 0.00637 -0.0992 0.3664 1.0000
2.000 0.7905 0.01292 0.00646 -0.0971 0.3526 1.0000
2.250 0.8078 0.01311 0.00656 -0.0951 0.3376 1.0000
2.500 0.8249 0.01332 0.00668 -0.0930 0.3207 1.0000
2.750 0.8420 0.01355 0.00680 -0.0910 0.3048 1.0000
3.000 0.8590 0.01380 0.00695 -0.0890 0.2895 1.0000
3.250 0.8756 0.01408 0.00713 -0.0869 0.2744 1.0000
3.500 0.8922 0.01437 0.00732 -0.0849 0.2635 1.0000
3.750 0.9103 0.01460 0.00751 -0.0830 0.2554 1.0000
4.000 0.9265 0.01492 0.00774 -0.0809 0.2475 1.0000
4.250 0.9453 0.01513 0.00795 -0.0793 0.2421 1.0000
4.500 0.9633 0.01539 0.00817 -0.0776 0.2366 1.0000
4.750 0.9800 0.01573 0.00845 -0.0756 0.2312 1.0000
5.000 0.9989 0.01597 0.00869 -0.0741 0.2274 1.0000
5.250 1.0179 0.01620 0.00893 -0.0726 0.2246 1.0000
5.500 1.0357 0.01649 0.00921 -0.0709 0.2209 1.0000
5.750 1.0527 0.01684 0.00951 -0.0691 0.2174 1.0000
6.000 1.0688 0.01725 0.00989 -0.0672 0.2137 1.0000
6.250 1.0882 0.01749 0.01017 -0.0659 0.2121 1.0000
6.500 1.1072 0.01775 0.01046 -0.0645 0.2098 1.0000
6.750 1.1257 0.01804 0.01077 -0.0631 0.2074 1.0000
7.000 1.1435 0.01837 0.01111 -0.0615 0.2057 1.0000
7.250 1.1607 0.01874 0.01148 -0.0599 0.2034 1.0000
7.500 1.1777 0.01914 0.01187 -0.0583 0.2012 1.0000
7.750 1.1945 0.01968 0.01238 -0.0568 0.1982 1.0000
8.000 1.2132 0.01995 0.01272 -0.0555 0.1970 1.0000
8.250 1.2316 0.02027 0.01309 -0.0542 0.1957 1.0000
8.500 1.2497 0.02063 0.01349 -0.0529 0.1944 1.0000
8.750 1.2675 0.02099 0.01390 -0.0515 0.1928 1.0000
9.000 1.2853 0.02138 0.01432 -0.0502 0.1913 1.0000
9.250 1.3024 0.02176 0.01473 -0.0489 0.1893 1.0000
9.500 1.3201 0.02219 0.01520 -0.0476 0.1885 1.0000
9.750 1.3371 0.02266 0.01568 -0.0463 0.1870 1.0000
10.000 1.3542 0.02324 0.01624 -0.0451 0.1841 1.0000
10.250 1.3708 0.02370 0.01675 -0.0438 0.1820 1.0000
10.500 1.3869 0.02410 0.01724 -0.0424 0.1807 1.0000
10.750 1.4011 0.02449 0.01771 -0.0407 0.1783 1.0000
11.000 1.4164 0.02493 0.01819 -0.0393 0.1762 1.0000
11.250 1.4324 0.02543 0.01876 -0.0380 0.1752 1.0000
11.500 1.4459 0.02595 0.01931 -0.0364 0.1727 1.0000
11.750 1.4602 0.02655 0.01993 -0.0350 0.1708 1.0000
12.000 1.4759 0.02731 0.02068 -0.0339 0.1681 1.0000
12.250 1.4891 0.02783 0.02132 -0.0324 0.1670 1.0000
12.500 1.5013 0.02837 0.02196 -0.0308 0.1647 1.0000
12.750 1.5154 0.02899 0.02267 -0.0295 0.1634 1.0000
13.000 1.5275 0.02961 0.02336 -0.0280 0.1607 1.0000
13.250 1.5393 0.03033 0.02412 -0.0266 0.1586 1.0000
13.500 1.5503 0.03116 0.02499 -0.0251 0.1565 1.0000
13.750 1.5605 0.03212 0.02597 -0.0236 0.1540 1.0000
14.000 1.5726 0.03284 0.02683 -0.0224 0.1523 1.0000
14.250 1.5844 0.03360 0.02770 -0.0213 0.1491 1.0000
14.500 1.5957 0.03445 0.02863 -0.0202 0.1462 1.0000
14.750 1.6032 0.03558 0.02977 -0.0188 0.1423 1.0000
15.000 1.6125 0.03665 0.03093 -0.0176 0.1394 1.0000
15.250 1.6256 0.03747 0.03186 -0.0169 0.1346 1.0000
15.500 1.6309 0.03889 0.03329 -0.0156 0.1290 1.0000
15.750 1.6404 0.04005 0.03450 -0.0147 0.1197 1.0000
16.000 1.6390 0.04216 0.03656 -0.0132 0.1053 1.0000
16.250 1.6244 0.04555 0.03983 -0.0110 0.0857 1.0000
16.500 1.5881 0.05133 0.04550 -0.0084 0.0625 1.0000
16.750 1.5657 0.05615 0.05032 -0.0072 0.0506 1.0000
17.000 1.5380 0.06196 0.05618 -0.0066 0.0406 1.0000
17.250 1.5245 0.06638 0.06072 -0.0068 0.0375 1.0000
17.500 1.4930 0.07343 0.06787 -0.0075 0.0319 1.0000
17.750 1.4606 0.08108 0.07565 -0.0091 0.0285 1.0000
18.000 1.4414 0.08710 0.08183 -0.0106 0.0281 1.0000
18.250 1.4070 0.09548 0.09035 -0.0129 0.0263 1.0000
18.500 1.3802 0.10283 0.09786 -0.0150 0.0259 1.0000
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