USA 45 M AIRFOIL (usa45m-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: USA 45 M AIRFOIL (usa45m-il) Reynolds number: 100,000 Max Cl/Cd: 45.11 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa45m-il-100000.txt Download as CSV file: xf-usa45m-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3625 0.09189 0.08713 -0.0260 1.0000 0.1087
-8.250 -0.3866 0.08921 0.08458 -0.0306 1.0000 0.1116
-8.000 -0.4231 0.08662 0.08205 -0.0354 1.0000 0.1124
-7.750 -0.3876 0.08216 0.07768 -0.0295 1.0000 0.1160
-7.500 -0.3822 0.07973 0.07530 -0.0278 1.0000 0.1200
-7.250 -0.3943 0.07679 0.07242 -0.0292 1.0000 0.1246
-7.000 -0.4405 0.07481 0.07021 -0.0334 1.0000 0.1282
-6.750 -0.4049 0.07070 0.06643 -0.0282 1.0000 0.1330
-6.500 -0.4097 0.06846 0.06421 -0.0272 1.0000 0.1399
-6.250 -0.4278 0.06542 0.06108 -0.0271 1.0000 0.1453
-6.000 -0.4180 0.06345 0.05926 -0.0234 1.0000 0.1502
-5.750 -0.4357 0.06134 0.05694 -0.0231 1.0000 0.1604
-5.500 -0.4283 0.05903 0.05481 -0.0195 1.0000 0.1639
-5.250 -0.4368 0.05729 0.05290 -0.0184 1.0000 0.1762
-5.000 -0.4166 0.05486 0.05061 -0.0180 0.9964 0.1856
-4.750 -0.3771 0.05128 0.04697 -0.0232 0.9854 0.2115
-4.500 -0.3380 0.04853 0.04420 -0.0269 0.9735 0.2444
-3.500 -0.1368 0.02914 0.02175 -0.0487 0.9239 0.1239
-3.250 -0.0891 0.02730 0.01917 -0.0506 0.9088 0.1122
-3.000 -0.0490 0.02468 0.01641 -0.0522 0.8902 0.1077
-2.750 -0.0100 0.02295 0.01435 -0.0529 0.8679 0.1035
-2.500 0.0283 0.02159 0.01267 -0.0534 0.8441 0.1013
-2.250 0.0608 0.02049 0.01139 -0.0530 0.8150 0.1016
-2.000 0.0899 0.01964 0.01040 -0.0522 0.7835 0.1048
-1.750 0.1172 0.01896 0.00957 -0.0512 0.7523 0.1070
-1.500 0.1430 0.01841 0.00888 -0.0499 0.7227 0.1087
-1.250 0.1678 0.01800 0.00831 -0.0486 0.6962 0.1111
-1.000 0.1914 0.01757 0.00775 -0.0473 0.6738 0.1148
-0.750 0.2152 0.01729 0.00736 -0.0461 0.6537 0.1231
-0.500 0.2394 0.01705 0.00703 -0.0450 0.6353 0.1371
-0.250 0.3747 0.01456 0.00681 -0.0634 0.6075 1.0000
0.000 0.3965 0.01477 0.00675 -0.0622 0.5937 1.0000
0.250 0.4182 0.01500 0.00678 -0.0611 0.5807 1.0000
0.500 0.4402 0.01525 0.00685 -0.0600 0.5689 1.0000
0.750 0.4626 0.01553 0.00691 -0.0590 0.5586 1.0000
1.000 0.4849 0.01580 0.00704 -0.0580 0.5485 1.0000
1.250 0.5072 0.01612 0.00724 -0.0570 0.5390 1.0000
1.500 0.5304 0.01643 0.00737 -0.0561 0.5307 1.0000
1.750 0.5523 0.01677 0.00768 -0.0551 0.5214 1.0000
2.000 0.5761 0.01713 0.00785 -0.0542 0.5144 1.0000
2.250 0.5978 0.01751 0.00825 -0.0532 0.5057 1.0000
2.500 0.6217 0.01789 0.00846 -0.0524 0.4991 1.0000
2.750 0.6433 0.01831 0.00893 -0.0514 0.4909 1.0000
3.000 0.6671 0.01870 0.00922 -0.0506 0.4844 1.0000
3.250 0.6889 0.01919 0.00973 -0.0496 0.4772 1.0000
3.500 0.7121 0.01961 0.01010 -0.0488 0.4704 1.0000
3.750 0.7348 0.02011 0.01058 -0.0479 0.4639 1.0000
4.000 0.7568 0.02060 0.01111 -0.0469 0.4568 1.0000
4.250 0.7817 0.02108 0.01146 -0.0463 0.4513 1.0000
4.500 0.8014 0.02165 0.01219 -0.0451 0.4436 1.0000
4.750 0.8255 0.02210 0.01258 -0.0444 0.4375 1.0000
5.000 0.8460 0.02273 0.01331 -0.0432 0.4306 1.0000
5.250 0.8687 0.02322 0.01381 -0.0424 0.4238 1.0000
5.500 0.8915 0.02380 0.01439 -0.0415 0.4176 1.0000
5.750 0.9118 0.02439 0.01511 -0.0404 0.4100 1.0000
6.000 0.9380 0.02482 0.01543 -0.0399 0.4044 1.0000
6.250 0.9548 0.02558 0.01642 -0.0384 0.3963 1.0000
6.500 0.9800 0.02596 0.01677 -0.0378 0.3901 1.0000
6.750 0.9977 0.02679 0.01778 -0.0365 0.3826 1.0000
7.000 1.0214 0.02721 0.01822 -0.0357 0.3759 1.0000
7.250 1.0411 0.02797 0.01909 -0.0346 0.3690 1.0000
7.500 1.0621 0.02854 0.01978 -0.0335 0.3617 1.0000
7.750 1.0854 0.02910 0.02036 -0.0328 0.3555 1.0000
8.000 1.1019 0.02996 0.02144 -0.0313 0.3478 1.0000
8.250 1.1290 0.03008 0.02148 -0.0309 0.3411 1.0000
8.500 1.1465 0.03025 0.02183 -0.0293 0.3307 1.0000
8.750 1.1667 0.03009 0.02171 -0.0279 0.3200 1.0000
9.000 1.1938 0.02942 0.02091 -0.0273 0.3103 1.0000
9.250 1.2117 0.02928 0.02089 -0.0256 0.2997 1.0000
9.500 1.2285 0.02942 0.02120 -0.0240 0.2902 1.0000
9.750 1.2493 0.02891 0.02066 -0.0226 0.2797 1.0000
10.000 1.2660 0.02864 0.02047 -0.0207 0.2689 1.0000
10.250 1.2770 0.02865 0.02067 -0.0182 0.2571 1.0000
10.500 1.2879 0.02867 0.02087 -0.0157 0.2451 1.0000
10.750 1.2947 0.02870 0.02101 -0.0127 0.2296 1.0000
11.000 1.2991 0.02906 0.02145 -0.0096 0.2127 1.0000
11.250 1.2984 0.02983 0.02225 -0.0060 0.1949 1.0000
11.500 1.2964 0.03103 0.02348 -0.0027 0.1749 1.0000
11.750 1.2884 0.03287 0.02526 0.0002 0.1523 1.0000
12.000 1.2773 0.03533 0.02768 0.0025 0.1313 1.0000
12.250 1.2600 0.03875 0.03104 0.0039 0.1085 1.0000
12.500 1.2398 0.04306 0.03532 0.0041 0.0890 1.0000
12.750 1.2159 0.04846 0.04072 0.0031 0.0770 1.0000
13.000 1.1970 0.05384 0.04618 0.0015 0.0727 1.0000
13.250 1.1752 0.05993 0.05233 -0.0005 0.0695 1.0000
13.500 1.1558 0.06588 0.05837 -0.0026 0.0673 1.0000
13.750 1.1370 0.07181 0.06437 -0.0046 0.0652 1.0000
14.000 1.1190 0.07774 0.07037 -0.0067 0.0635 1.0000
14.250 1.1027 0.08355 0.07623 -0.0087 0.0619 1.0000
14.500 1.0891 0.08911 0.08188 -0.0107 0.0600 1.0000
14.750 1.0771 0.09453 0.08737 -0.0127 0.0582 1.0000
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Polar data table (+)
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