USA 45 M AIRFOIL (usa45m-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: USA 45 M AIRFOIL (usa45m-il) Reynolds number: 50,000 Max Cl/Cd: 29.5 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa45m-il-50000-n5.txt Download as CSV file: xf-usa45m-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 45 M AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3838 0.10206 0.09540 -0.0234 1.0000 0.1691
-8.500 -0.3595 0.09776 0.09107 -0.0209 1.0000 0.1765
-8.250 -0.3875 0.09644 0.08997 -0.0238 1.0000 0.1848
-8.000 -0.3589 0.09223 0.08572 -0.0210 1.0000 0.1932
-7.500 -0.3648 0.08685 0.08054 -0.0204 1.0000 0.2080
-7.000 -0.4202 0.07046 0.06390 -0.0358 1.0000 0.0915
-6.750 -0.4135 0.06734 0.06084 -0.0343 1.0000 0.0887
-6.500 -0.4141 0.06388 0.05734 -0.0334 1.0000 0.0855
-6.250 -0.4276 0.05919 0.05193 -0.0330 1.0000 0.0782
-6.000 -0.4204 0.05631 0.04908 -0.0314 1.0000 0.0774
-5.750 -0.4161 0.05365 0.04628 -0.0296 1.0000 0.0772
-5.500 -0.4116 0.05118 0.04355 -0.0277 1.0000 0.0775
-5.250 -0.4059 0.04889 0.04095 -0.0258 1.0000 0.0778
-5.000 -0.3736 0.04553 0.03720 -0.0287 0.9887 0.0776
-4.750 -0.3364 0.04228 0.03360 -0.0321 0.9751 0.0768
-4.500 -0.2986 0.03941 0.03030 -0.0350 0.9610 0.0763
-4.250 -0.2603 0.03691 0.02736 -0.0376 0.9462 0.0761
-4.000 -0.2215 0.03479 0.02479 -0.0398 0.9308 0.0767
-3.750 -0.1817 0.03300 0.02254 -0.0420 0.9148 0.0787
-3.500 -0.1428 0.03101 0.02036 -0.0441 0.8984 0.0804
-3.250 -0.1066 0.02950 0.01861 -0.0452 0.8786 0.0811
-3.000 -0.0692 0.02811 0.01704 -0.0464 0.8583 0.0820
-2.750 -0.0305 0.02686 0.01560 -0.0476 0.8378 0.0833
-2.500 0.0046 0.02584 0.01443 -0.0481 0.8139 0.0851
-2.250 0.0406 0.02497 0.01338 -0.0487 0.7905 0.0890
-2.000 0.0727 0.02430 0.01247 -0.0486 0.7644 0.0933
-1.750 0.1029 0.02355 0.01161 -0.0485 0.7400 0.0973
-1.500 0.1294 0.02307 0.01092 -0.0476 0.7153 0.1011
-1.250 0.1554 0.02269 0.01029 -0.0467 0.6925 0.1061
-1.000 0.1800 0.02229 0.00979 -0.0457 0.6707 0.1140
-0.750 0.2045 0.02190 0.00935 -0.0448 0.6514 0.1323
-0.500 0.3147 0.01894 0.00905 -0.0583 0.6247 1.0000
-0.250 0.3363 0.01915 0.00888 -0.0570 0.6082 1.0000
0.250 0.3799 0.01962 0.00874 -0.0546 0.5798 1.0000
0.500 0.4022 0.01988 0.00872 -0.0535 0.5674 1.0000
0.750 0.4252 0.02016 0.00879 -0.0526 0.5557 1.0000
1.000 0.4481 0.02047 0.00892 -0.0518 0.5444 1.0000
1.250 0.4715 0.02078 0.00904 -0.0510 0.5344 1.0000
1.500 0.4947 0.02111 0.00921 -0.0501 0.5248 1.0000
1.750 0.5176 0.02148 0.00946 -0.0493 0.5155 1.0000
2.000 0.5414 0.02183 0.00964 -0.0485 0.5075 1.0000
2.250 0.5637 0.02225 0.01000 -0.0476 0.4985 1.0000
2.500 0.5876 0.02262 0.01023 -0.0469 0.4915 1.0000
2.750 0.6095 0.02310 0.01070 -0.0460 0.4831 1.0000
3.000 0.6333 0.02351 0.01098 -0.0452 0.4764 1.0000
3.250 0.6550 0.02403 0.01153 -0.0443 0.4685 1.0000
3.500 0.6784 0.02448 0.01191 -0.0435 0.4619 1.0000
3.750 0.7004 0.02504 0.01247 -0.0427 0.4550 1.0000
4.000 0.7228 0.02557 0.01301 -0.0418 0.4482 1.0000
4.250 0.7460 0.02609 0.01348 -0.0410 0.4420 1.0000
4.500 0.7667 0.02675 0.01423 -0.0401 0.4348 1.0000
4.750 0.7909 0.02724 0.01466 -0.0394 0.4291 1.0000
5.000 0.8102 0.02800 0.01555 -0.0383 0.4218 1.0000
5.250 0.8327 0.02858 0.01614 -0.0375 0.4155 1.0000
5.500 0.8539 0.02927 0.01688 -0.0366 0.4092 1.0000
5.750 0.8736 0.03001 0.01776 -0.0356 0.4020 1.0000
6.000 0.8988 0.03047 0.01816 -0.0350 0.3968 1.0000
6.250 0.9137 0.03152 0.01945 -0.0336 0.3888 1.0000
6.500 0.9369 0.03205 0.02001 -0.0328 0.3828 1.0000
6.750 0.9531 0.03306 0.02120 -0.0315 0.3757 1.0000
7.000 0.9732 0.03376 0.02199 -0.0305 0.3689 1.0000
7.250 0.9925 0.03455 0.02288 -0.0295 0.3626 1.0000
7.500 1.0075 0.03562 0.02416 -0.0281 0.3553 1.0000
7.750 1.0338 0.03591 0.02444 -0.0276 0.3500 1.0000
8.000 1.0396 0.03757 0.02642 -0.0255 0.3418 1.0000
8.250 1.0623 0.03808 0.02699 -0.0247 0.3362 1.0000
8.500 1.0697 0.03968 0.02884 -0.0228 0.3292 1.0000
8.750 1.0856 0.04063 0.02996 -0.0215 0.3229 1.0000
9.000 1.1028 0.04156 0.03101 -0.0204 0.3175 1.0000
9.250 1.1011 0.04375 0.03348 -0.0180 0.3105 1.0000
9.500 1.1247 0.04419 0.03400 -0.0173 0.3057 1.0000
9.750 1.1126 0.04708 0.03714 -0.0145 0.2993 1.0000
10.000 1.1125 0.04912 0.03936 -0.0125 0.2937 1.0000
10.250 1.1472 0.04856 0.03891 -0.0121 0.2891 1.0000
10.500 1.0499 0.05823 0.04867 -0.0077 0.2822 1.0000
10.750 1.0453 0.06133 0.05187 -0.0072 0.2774 1.0000
11.000 0.9500 0.07728 0.06769 -0.0132 0.2643 1.0000
11.250 0.9681 0.07796 0.06850 -0.0123 0.2614 1.0000
11.750 0.9251 0.09203 0.08260 -0.0172 0.2473 1.0000
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Polar data table (+)
Polar graphs
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