Glenn Martin 3 (glennmartin3-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Glenn Martin 3 (glennmartin3-il) Reynolds number: 100,000 Max Cl/Cd: 38.37 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-glennmartin3-il-100000-n5.txt Download as CSV file: xf-glennmartin3-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4186 0.08417 0.07946 -0.0523 0.9716 0.0387
-8.250 -0.4331 0.08041 0.07565 -0.0514 0.9661 0.0387
-8.000 -0.4494 0.07472 0.06981 -0.0512 0.9596 0.0388
-7.500 -0.4669 0.06527 0.05996 -0.0475 0.9477 0.0388
-7.250 -0.4799 0.06078 0.05518 -0.0434 0.9398 0.0388
-6.750 -0.4657 0.05698 0.05125 -0.0390 0.9295 0.0401
-6.500 -0.4642 0.05288 0.04678 -0.0360 0.9249 0.0402
-6.250 -0.4624 0.05103 0.04477 -0.0321 0.9187 0.0410
-5.750 -0.4476 0.04519 0.03812 -0.0257 0.9101 0.0433
-5.500 -0.4503 0.04320 0.03580 -0.0200 0.9023 0.0435
-5.250 -0.4379 0.04090 0.03304 -0.0169 0.8981 0.0439
-5.000 -0.4260 0.03871 0.03021 -0.0133 0.8937 0.0461
-4.750 -0.4128 0.03775 0.02923 -0.0106 0.8863 0.0474
-4.500 -0.3864 0.03623 0.02742 -0.0100 0.8819 0.0482
-4.250 -0.3628 0.03484 0.02574 -0.0087 0.8767 0.0494
-4.000 -0.3442 0.03374 0.02437 -0.0065 0.8695 0.0507
-3.750 -0.3111 0.03256 0.02276 -0.0068 0.8653 0.0532
-3.500 -0.2697 0.03109 0.02119 -0.0091 0.8626 0.0550
-3.250 -0.2547 0.03049 0.02050 -0.0065 0.8531 0.0557
-3.000 -0.2177 0.02957 0.01951 -0.0080 0.8489 0.0580
-2.750 -0.1741 0.02861 0.01840 -0.0106 0.8459 0.0612
-2.500 -0.1536 0.02807 0.01776 -0.0089 0.8358 0.0626
-2.250 -0.1134 0.02702 0.01679 -0.0111 0.8313 0.0654
-2.000 -0.0718 0.02615 0.01592 -0.0134 0.8283 0.0694
-1.750 -0.0541 0.02588 0.01559 -0.0112 0.8181 0.0730
-1.500 -0.0172 0.02509 0.01484 -0.0127 0.8135 0.0779
-1.250 0.3274 0.02076 0.01391 -0.0791 0.8275 0.9362
-1.000 0.3783 0.02167 0.01457 -0.0833 0.8150 1.0000
-0.750 0.4058 0.02127 0.01400 -0.0827 0.8017 1.0000
-0.500 0.4365 0.02085 0.01342 -0.0828 0.7886 1.0000
-0.250 0.4628 0.02057 0.01300 -0.0821 0.7722 1.0000
0.000 0.4837 0.02044 0.01274 -0.0804 0.7513 1.0000
0.250 0.5104 0.02017 0.01233 -0.0798 0.7271 1.0000
0.500 0.5428 0.01979 0.01175 -0.0802 0.6950 1.0000
0.750 0.5965 0.01905 0.01062 -0.0847 0.6475 1.0000
1.000 0.6421 0.01880 0.00989 -0.0879 0.5923 1.0000
1.250 0.6689 0.01899 0.00971 -0.0877 0.5429 1.0000
1.500 0.6885 0.01934 0.00971 -0.0860 0.4977 1.0000
1.750 0.7058 0.01975 0.00979 -0.0840 0.4662 1.0000
2.000 0.7238 0.02012 0.00994 -0.0822 0.4440 1.0000
2.250 0.7420 0.02050 0.01011 -0.0804 0.4244 1.0000
2.500 0.7605 0.02086 0.01032 -0.0788 0.4080 1.0000
2.750 0.7792 0.02123 0.01054 -0.0772 0.3930 1.0000
3.000 0.7978 0.02157 0.01078 -0.0756 0.3788 1.0000
3.250 0.8157 0.02192 0.01105 -0.0738 0.3643 1.0000
3.500 0.8336 0.02228 0.01131 -0.0721 0.3511 1.0000
3.750 0.8509 0.02267 0.01159 -0.0703 0.3392 1.0000
4.000 0.8685 0.02303 0.01189 -0.0686 0.3272 1.0000
4.250 0.8859 0.02342 0.01221 -0.0669 0.3162 1.0000
4.500 0.9029 0.02384 0.01253 -0.0651 0.3070 1.0000
4.750 0.9217 0.02422 0.01288 -0.0636 0.2984 1.0000
5.000 0.9388 0.02467 0.01324 -0.0619 0.2909 1.0000
5.250 0.9580 0.02508 0.01362 -0.0607 0.2844 1.0000
5.500 0.9762 0.02552 0.01403 -0.0592 0.2778 1.0000
5.750 0.9942 0.02602 0.01443 -0.0578 0.2729 1.0000
6.000 1.0138 0.02644 0.01489 -0.0566 0.2672 1.0000
6.250 1.0330 0.02692 0.01536 -0.0554 0.2626 1.0000
6.500 1.0512 0.02743 0.01582 -0.0541 0.2584 1.0000
6.750 1.0709 0.02793 0.01631 -0.0531 0.2543 1.0000
7.000 1.0906 0.02843 0.01685 -0.0521 0.2502 1.0000
7.250 1.1100 0.02895 0.01739 -0.0511 0.2466 1.0000
7.500 1.1299 0.02949 0.01794 -0.0502 0.2435 1.0000
7.750 1.1512 0.03007 0.01847 -0.0495 0.2409 1.0000
8.000 1.1722 0.03066 0.01911 -0.0489 0.2382 1.0000
8.250 1.1918 0.03125 0.01982 -0.0480 0.2354 1.0000
8.500 1.2113 0.03185 0.02050 -0.0471 0.2327 1.0000
8.750 1.2291 0.03246 0.02116 -0.0460 0.2296 1.0000
9.000 1.2493 0.03310 0.02184 -0.0453 0.2273 1.0000
9.250 1.2704 0.03376 0.02249 -0.0448 0.2250 1.0000
9.500 1.2923 0.03448 0.02325 -0.0445 0.2229 1.0000
9.750 1.3086 0.03523 0.02417 -0.0432 0.2210 1.0000
10.000 1.3252 0.03603 0.02514 -0.0420 0.2191 1.0000
10.250 1.3414 0.03687 0.02612 -0.0408 0.2170 1.0000
10.500 1.3575 0.03771 0.02708 -0.0396 0.2151 1.0000
10.750 1.3730 0.03852 0.02799 -0.0384 0.2131 1.0000
11.000 1.3896 0.03934 0.02890 -0.0373 0.2110 1.0000
11.250 1.4089 0.04014 0.02975 -0.0368 0.2092 1.0000
11.500 1.4325 0.04103 0.03067 -0.0370 0.2075 1.0000
11.750 1.4383 0.04218 0.03204 -0.0344 0.2059 1.0000
12.000 1.4409 0.04344 0.03356 -0.0314 0.2041 1.0000
12.250 1.4439 0.04473 0.03507 -0.0287 0.2022 1.0000
12.500 1.4465 0.04606 0.03660 -0.0260 0.2001 1.0000
12.750 1.4509 0.04736 0.03808 -0.0237 0.1982 1.0000
13.000 1.4572 0.04869 0.03956 -0.0217 0.1966 1.0000
13.250 1.4662 0.04982 0.04082 -0.0201 0.1948 1.0000
13.500 1.4794 0.05089 0.04196 -0.0192 0.1931 1.0000
13.750 1.5012 0.05182 0.04291 -0.0193 0.1914 1.0000
14.000 1.4902 0.05397 0.04533 -0.0157 0.1903 1.0000
14.250 1.4688 0.05685 0.04853 -0.0116 0.1887 1.0000
14.500 1.4453 0.06018 0.05215 -0.0080 0.1870 1.0000
14.750 1.4210 0.06394 0.05617 -0.0051 0.1853 1.0000
15.000 1.3946 0.06815 0.06062 -0.0027 0.1834 1.0000
15.250 1.3721 0.07238 0.06504 -0.0012 0.1812 1.0000
15.500 1.3363 0.07864 0.07152 -0.0004 0.1799 1.0000
15.750 1.4361 0.07019 0.06274 -0.0013 0.1754 1.0000
16.000 1.3764 0.07866 0.07156 0.0003 0.1747 1.0000
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Polar data table (+)
Polar graphs
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