USA 46 AIRFOIL (usa46-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 46 AIRFOIL (usa46-il) Reynolds number: 50,000 Max Cl/Cd: 38.34 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa46-il-50000-n5.txt Download as CSV file: xf-usa46-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4966 0.09234 0.08550 -0.0148 1.0000 0.0467
-8.000 -0.4985 0.08809 0.08134 -0.0171 1.0000 0.0461
-7.750 -0.4999 0.08334 0.07670 -0.0205 1.0000 0.0454
-7.500 -0.4984 0.07778 0.07121 -0.0257 1.0000 0.0447
-6.750 -0.4764 0.06285 0.05625 -0.0375 1.0000 0.0470
-6.500 -0.4654 0.05751 0.05077 -0.0415 1.0000 0.0490
-6.250 -0.4521 0.05140 0.04440 -0.0459 1.0000 0.0509
-6.000 -0.4357 0.04490 0.03742 -0.0500 1.0000 0.0525
-5.750 -0.4154 0.03839 0.03012 -0.0531 1.0000 0.0547
-5.500 -0.3947 0.03591 0.02744 -0.0535 1.0000 0.0613
-5.250 -0.3701 0.03167 0.02228 -0.0546 1.0000 0.0694
-5.000 -0.3475 0.03008 0.02050 -0.0544 1.0000 0.0803
-4.750 -0.3236 0.02822 0.01833 -0.0541 1.0000 0.0913
-4.500 -0.2986 0.02611 0.01578 -0.0537 1.0000 0.1000
-4.250 -0.2747 0.02527 0.01473 -0.0533 1.0000 0.1146
-4.000 -0.2495 0.02386 0.01292 -0.0527 1.0000 0.1250
-3.750 -0.2254 0.02276 0.01167 -0.0519 1.0000 0.1345
-3.500 -0.2008 0.02190 0.01062 -0.0513 1.0000 0.1502
-3.250 -0.1768 0.02105 0.00959 -0.0505 1.0000 0.1669
-3.000 -0.1531 0.02023 0.00876 -0.0498 1.0000 0.1854
-2.750 -0.1285 0.01955 0.00797 -0.0493 1.0000 0.2101
-2.500 -0.1043 0.01888 0.00730 -0.0488 1.0000 0.2358
-2.250 -0.0801 0.01830 0.00677 -0.0483 1.0000 0.2677
-2.000 -0.0560 0.01769 0.00634 -0.0479 1.0000 0.3060
-1.750 -0.0320 0.01703 0.00597 -0.0476 1.0000 0.3662
-1.500 -0.0105 0.01612 0.00583 -0.0465 1.0000 0.5061
-1.250 0.0029 0.01533 0.00581 -0.0426 1.0000 0.7442
-1.000 0.0298 0.01479 0.00542 -0.0420 1.0000 1.0000
-0.750 0.0534 0.01493 0.00528 -0.0417 1.0000 1.0000
-0.500 0.0766 0.01511 0.00524 -0.0413 1.0000 1.0000
-0.250 0.0992 0.01533 0.00528 -0.0409 1.0000 1.0000
0.000 0.1213 0.01558 0.00538 -0.0405 1.0000 1.0000
0.250 0.1505 0.01590 0.00557 -0.0416 0.9950 1.0000
0.500 0.1937 0.01623 0.00582 -0.0453 0.9803 1.0000
0.750 0.2386 0.01653 0.00606 -0.0492 0.9644 1.0000
1.000 0.2852 0.01669 0.00621 -0.0530 0.9434 1.0000
1.250 0.3352 0.01676 0.00632 -0.0571 0.9220 1.0000
1.500 0.3799 0.01679 0.00640 -0.0599 0.9001 1.0000
1.750 0.4194 0.01687 0.00655 -0.0618 0.8794 1.0000
2.000 0.4562 0.01694 0.00674 -0.0630 0.8574 1.0000
2.250 0.4896 0.01705 0.00693 -0.0635 0.8334 1.0000
2.500 0.5218 0.01716 0.00714 -0.0637 0.8084 1.0000
2.750 0.5523 0.01728 0.00740 -0.0634 0.7823 1.0000
3.000 0.5812 0.01744 0.00765 -0.0629 0.7545 1.0000
3.250 0.6087 0.01764 0.00795 -0.0620 0.7252 1.0000
3.500 0.6354 0.01788 0.00834 -0.0610 0.6949 1.0000
3.750 0.6614 0.01816 0.00873 -0.0599 0.6631 1.0000
4.000 0.6871 0.01849 0.00917 -0.0587 0.6312 1.0000
4.250 0.7124 0.01889 0.00966 -0.0575 0.5990 1.0000
4.500 0.7370 0.01935 0.01030 -0.0561 0.5625 1.0000
4.750 0.7605 0.01984 0.01088 -0.0546 0.5208 1.0000
5.000 0.7783 0.02030 0.01120 -0.0519 0.4467 1.0000
5.250 0.7878 0.02155 0.01135 -0.0488 0.2885 1.0000
5.500 0.8014 0.02425 0.01284 -0.0474 0.1009 1.0000
5.750 0.8193 0.02673 0.01495 -0.0463 0.0624 1.0000
6.000 0.8387 0.02863 0.01708 -0.0449 0.0528 1.0000
6.250 0.8578 0.03055 0.01920 -0.0435 0.0469 1.0000
6.500 0.8772 0.03242 0.02121 -0.0422 0.0411 1.0000
6.750 0.8976 0.03468 0.02359 -0.0409 0.0384 1.0000
7.000 0.9214 0.03699 0.02622 -0.0396 0.0366 1.0000
7.250 0.9444 0.03954 0.02910 -0.0384 0.0345 1.0000
7.500 0.9645 0.04215 0.03195 -0.0375 0.0321 1.0000
7.750 0.9820 0.04542 0.03538 -0.0367 0.0304 1.0000
8.000 0.9978 0.04884 0.03936 -0.0353 0.0299 1.0000
8.250 1.0098 0.05265 0.04369 -0.0340 0.0296 1.0000
8.500 1.0175 0.05666 0.04831 -0.0327 0.0295 1.0000
8.750 1.0208 0.06084 0.05294 -0.0314 0.0295 1.0000
9.000 1.0200 0.06508 0.05756 -0.0304 0.0296 1.0000
9.250 1.0149 0.06939 0.06218 -0.0295 0.0297 1.0000
9.500 1.0054 0.07370 0.06675 -0.0290 0.0298 1.0000
9.750 0.9913 0.07781 0.07104 -0.0285 0.0299 1.0000
10.000 0.9764 0.08226 0.07563 -0.0293 0.0300 1.0000
10.250 0.9607 0.08746 0.08094 -0.0316 0.0302 1.0000
10.500 0.9469 0.09322 0.08678 -0.0350 0.0304 1.0000
10.750 0.9349 0.09954 0.09315 -0.0390 0.0305 1.0000
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Polar data table (+)
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