USA 46 AIRFOIL (usa46-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 46 AIRFOIL (usa46-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.77 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa46-il-1000000-n5.txt Download as CSV file: xf-usa46-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 46 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6916 0.07483 0.07320 -0.0183 1.0000 0.0028
-10.000 -0.7949 0.03196 0.02979 -0.0573 1.0000 0.0022
-9.750 -0.7845 0.02670 0.02411 -0.0596 1.0000 0.0023
-9.500 -0.7682 0.02364 0.02073 -0.0602 1.0000 0.0023
-9.250 -0.7492 0.02142 0.01823 -0.0603 1.0000 0.0024
-9.000 -0.7289 0.01956 0.01611 -0.0602 1.0000 0.0025
-8.750 -0.7074 0.01803 0.01433 -0.0599 1.0000 0.0026
-8.500 -0.6849 0.01688 0.01299 -0.0595 1.0000 0.0028
-8.250 -0.6621 0.01580 0.01173 -0.0591 1.0000 0.0029
-8.000 -0.6387 0.01492 0.01069 -0.0586 1.0000 0.0030
-7.750 -0.6155 0.01390 0.00951 -0.0580 1.0000 0.0031
-7.500 -0.5923 0.01289 0.00833 -0.0575 1.0000 0.0034
-7.250 -0.5684 0.01222 0.00757 -0.0569 1.0000 0.0035
-7.000 -0.5442 0.01168 0.00695 -0.0563 1.0000 0.0038
-6.750 -0.5137 0.01112 0.00630 -0.0571 0.9988 0.0041
-6.500 -0.4808 0.01063 0.00572 -0.0584 0.9967 0.0045
-6.250 -0.4477 0.01023 0.00523 -0.0596 0.9941 0.0049
-6.000 -0.4161 0.00963 0.00452 -0.0605 0.9905 0.0056
-5.750 -0.3839 0.00918 0.00402 -0.0616 0.9874 0.0063
-5.500 -0.3538 0.00883 0.00361 -0.0621 0.9832 0.0071
-5.250 -0.3225 0.00853 0.00325 -0.0628 0.9786 0.0079
-5.000 -0.2909 0.00812 0.00283 -0.0637 0.9736 0.0111
-4.750 -0.2586 0.00779 0.00250 -0.0647 0.9675 0.0193
-4.500 -0.2259 0.00750 0.00226 -0.0658 0.9597 0.0307
-4.250 -0.1915 0.00732 0.00205 -0.0672 0.9498 0.0352
-4.000 -0.1576 0.00712 0.00184 -0.0684 0.9352 0.0407
-3.750 -0.1267 0.00702 0.00165 -0.0690 0.9136 0.0437
-3.500 -0.0992 0.00691 0.00148 -0.0687 0.8896 0.0512
-3.250 -0.0726 0.00686 0.00134 -0.0683 0.8677 0.0553
-3.000 -0.0461 0.00678 0.00120 -0.0679 0.8470 0.0634
-2.750 -0.0197 0.00673 0.00107 -0.0675 0.8256 0.0726
-2.500 0.0068 0.00666 0.00096 -0.0670 0.8026 0.0857
-2.250 0.0331 0.00659 0.00087 -0.0667 0.7787 0.1063
-2.000 0.0596 0.00658 0.00081 -0.0663 0.7540 0.1216
-1.750 0.0862 0.00660 0.00076 -0.0659 0.7275 0.1312
-1.500 0.1127 0.00666 0.00070 -0.0655 0.6970 0.1382
-1.250 0.1392 0.00672 0.00067 -0.0651 0.6635 0.1450
-1.000 0.1659 0.00680 0.00064 -0.0648 0.6319 0.1509
-0.750 0.1928 0.00685 0.00061 -0.0645 0.6071 0.1570
-0.500 0.2198 0.00689 0.00060 -0.0643 0.5851 0.1669
-0.250 0.2468 0.00691 0.00060 -0.0641 0.5624 0.1825
0.000 0.2736 0.00693 0.00061 -0.0638 0.5385 0.2048
0.250 0.3006 0.00692 0.00062 -0.0637 0.5195 0.2335
0.500 0.3276 0.00683 0.00064 -0.0635 0.5059 0.2877
0.750 0.3545 0.00668 0.00067 -0.0634 0.4926 0.3672
1.000 0.3813 0.00656 0.00072 -0.0632 0.4761 0.4454
1.250 0.4077 0.00649 0.00078 -0.0630 0.4533 0.5224
1.500 0.4336 0.00646 0.00086 -0.0626 0.4180 0.6023
1.750 0.4576 0.00661 0.00102 -0.0620 0.3523 0.6935
2.000 0.4827 0.00680 0.00118 -0.0614 0.3125 0.7477
2.250 0.5091 0.00687 0.00128 -0.0610 0.2978 0.7762
2.500 0.5350 0.00705 0.00141 -0.0606 0.2671 0.7979
2.750 0.5608 0.00717 0.00152 -0.0602 0.2438 0.8215
3.000 0.5840 0.00723 0.00164 -0.0591 0.2068 0.8768
3.250 0.6177 0.00780 0.00196 -0.0608 0.1125 1.0000
3.500 0.6423 0.00836 0.00226 -0.0603 0.0549 1.0000
3.750 0.6676 0.00882 0.00256 -0.0598 0.0196 1.0000
4.000 0.6941 0.00907 0.00279 -0.0595 0.0121 1.0000
4.250 0.7207 0.00929 0.00305 -0.0592 0.0105 1.0000
4.500 0.7470 0.00956 0.00333 -0.0589 0.0090 1.0000
4.750 0.7727 0.00995 0.00375 -0.0584 0.0070 1.0000
5.000 0.7989 0.01022 0.00405 -0.0581 0.0064 1.0000
5.250 0.8249 0.01053 0.00440 -0.0577 0.0058 1.0000
5.500 0.8506 0.01088 0.00479 -0.0572 0.0052 1.0000
5.750 0.8758 0.01131 0.00524 -0.0568 0.0048 1.0000
6.000 0.9000 0.01195 0.00596 -0.0561 0.0043 1.0000
6.250 0.9251 0.01237 0.00643 -0.0556 0.0041 1.0000
6.500 0.9501 0.01278 0.00689 -0.0551 0.0037 1.0000
6.750 0.9746 0.01328 0.00744 -0.0545 0.0034 1.0000
7.000 0.9988 0.01381 0.00802 -0.0539 0.0032 1.0000
7.250 1.0225 0.01442 0.00872 -0.0533 0.0030 1.0000
7.500 1.0458 0.01505 0.00941 -0.0526 0.0029 1.0000
7.750 1.0661 0.01622 0.01070 -0.0514 0.0026 1.0000
8.000 1.0883 0.01705 0.01164 -0.0506 0.0026 1.0000
8.250 1.1102 0.01792 0.01262 -0.0497 0.0025 1.0000
8.500 1.1309 0.01899 0.01384 -0.0486 0.0024 1.0000
8.750 1.1505 0.02029 0.01531 -0.0474 0.0023 1.0000
9.000 1.1690 0.02177 0.01698 -0.0461 0.0021 1.0000
9.250 1.1856 0.02359 0.01903 -0.0446 0.0020 1.0000
9.500 1.1994 0.02590 0.02162 -0.0429 0.0020 1.0000
9.750 1.2091 0.02883 0.02489 -0.0407 0.0019 1.0000
10.000 1.2092 0.03321 0.02972 -0.0377 0.0019 1.0000
10.250 1.2100 0.03670 0.03353 -0.0352 0.0018 1.0000
10.500 1.1908 0.04242 0.03969 -0.0313 0.0018 1.0000
10.750 1.1751 0.04554 0.04302 -0.0274 0.0017 1.0000
11.000 1.1471 0.05010 0.04781 -0.0246 0.0018 1.0000
11.250 1.1246 0.05490 0.05279 -0.0246 0.0017 1.0000
11.500 1.1063 0.06018 0.05822 -0.0269 0.0017 1.0000
11.750 1.0478 0.07551 0.07385 -0.0372 0.0019 1.0000
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