USA 46 AIRFOIL (usa46-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: USA 46 AIRFOIL (usa46-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.25 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa46-il-1000000.txt Download as CSV file: xf-usa46-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.7109 0.02778 0.02533 -0.0583 1.0000 0.0065
-8.750 -0.6949 0.02441 0.02160 -0.0591 1.0000 0.0067
-8.500 -0.6762 0.02192 0.01879 -0.0592 1.0000 0.0069
-8.250 -0.6548 0.02043 0.01708 -0.0589 1.0000 0.0071
-8.000 -0.6323 0.01932 0.01580 -0.0585 1.0000 0.0072
-7.750 -0.6139 0.01622 0.01223 -0.0582 1.0000 0.0075
-7.500 -0.5933 0.01404 0.00972 -0.0576 1.0000 0.0079
-7.250 -0.5700 0.01310 0.00865 -0.0570 1.0000 0.0084
-7.000 -0.5461 0.01246 0.00792 -0.0564 1.0000 0.0090
-6.750 -0.5219 0.01198 0.00737 -0.0558 1.0000 0.0097
-6.500 -0.4977 0.01149 0.00679 -0.0551 1.0000 0.0104
-6.250 -0.4734 0.01107 0.00630 -0.0544 1.0000 0.0109
-6.000 -0.4500 0.01005 0.00510 -0.0536 1.0000 0.0118
-5.750 -0.4261 0.00946 0.00444 -0.0528 1.0000 0.0133
-5.500 -0.4021 0.00913 0.00406 -0.0520 1.0000 0.0147
-5.250 -0.3730 0.00885 0.00373 -0.0523 0.9993 0.0161
-5.000 -0.3389 0.00834 0.00321 -0.0537 0.9975 0.0213
-4.750 -0.3043 0.00802 0.00290 -0.0552 0.9955 0.0282
-4.500 -0.2696 0.00792 0.00279 -0.0567 0.9935 0.0325
-4.250 -0.2367 0.00759 0.00247 -0.0578 0.9905 0.0392
-4.000 -0.2027 0.00746 0.00233 -0.0591 0.9875 0.0433
-3.750 -0.1676 0.00719 0.00205 -0.0606 0.9847 0.0492
-3.500 -0.1332 0.00699 0.00185 -0.0620 0.9805 0.0551
-3.250 -0.0993 0.00673 0.00163 -0.0632 0.9739 0.0663
-3.000 -0.0639 0.00648 0.00143 -0.0648 0.9672 0.0821
-2.750 -0.0292 0.00621 0.00129 -0.0663 0.9575 0.1133
-2.500 0.0056 0.00608 0.00118 -0.0677 0.9439 0.1333
-2.250 0.0379 0.00599 0.00108 -0.0685 0.9249 0.1449
-2.000 0.0666 0.00597 0.00100 -0.0684 0.9046 0.1543
-1.750 0.0938 0.00596 0.00092 -0.0681 0.8850 0.1626
-1.500 0.1205 0.00594 0.00086 -0.0676 0.8649 0.1703
-1.250 0.1470 0.00596 0.00080 -0.0671 0.8435 0.1778
-1.000 0.1736 0.00593 0.00075 -0.0667 0.8228 0.1898
-0.750 0.2003 0.00590 0.00071 -0.0663 0.8032 0.2056
-0.500 0.2267 0.00581 0.00067 -0.0659 0.7818 0.2427
-0.250 0.2521 0.00548 0.00065 -0.0655 0.7580 0.3777
0.000 0.2767 0.00505 0.00068 -0.0650 0.7328 0.5632
0.250 0.3012 0.00485 0.00074 -0.0642 0.7055 0.6844
0.500 0.3265 0.00488 0.00079 -0.0635 0.6738 0.7423
0.750 0.3524 0.00497 0.00083 -0.0629 0.6429 0.7726
1.000 0.3783 0.00505 0.00087 -0.0623 0.6138 0.7955
1.250 0.4041 0.00512 0.00091 -0.0617 0.5860 0.8184
1.500 0.4292 0.00513 0.00095 -0.0610 0.5620 0.8507
1.750 0.4668 0.00502 0.00099 -0.0631 0.5299 1.0000
2.000 0.4936 0.00518 0.00106 -0.0627 0.5062 1.0000
2.250 0.5203 0.00535 0.00114 -0.0624 0.4783 1.0000
2.500 0.5459 0.00566 0.00123 -0.0620 0.4190 1.0000
2.750 0.5705 0.00612 0.00137 -0.0614 0.3465 1.0000
3.000 0.5963 0.00645 0.00153 -0.0610 0.3079 1.0000
3.250 0.6225 0.00672 0.00169 -0.0607 0.2765 1.0000
3.500 0.6486 0.00699 0.00184 -0.0604 0.2441 1.0000
3.750 0.6740 0.00739 0.00203 -0.0599 0.1967 1.0000
4.000 0.6953 0.00845 0.00251 -0.0591 0.0727 1.0000
4.250 0.7192 0.00918 0.00298 -0.0583 0.0198 1.0000
4.500 0.7451 0.00954 0.00334 -0.0579 0.0161 1.0000
4.750 0.7705 0.01004 0.00394 -0.0572 0.0138 1.0000
5.000 0.7965 0.01037 0.00431 -0.0568 0.0132 1.0000
5.250 0.8221 0.01075 0.00472 -0.0563 0.0119 1.0000
5.500 0.8474 0.01119 0.00520 -0.0558 0.0109 1.0000
5.750 0.8717 0.01180 0.00586 -0.0551 0.0101 1.0000
6.000 0.8931 0.01295 0.00714 -0.0539 0.0093 1.0000
6.250 0.9152 0.01396 0.00824 -0.0528 0.0089 1.0000
6.500 0.9398 0.01447 0.00881 -0.0522 0.0085 1.0000
6.750 0.9633 0.01525 0.00966 -0.0514 0.0081 1.0000
7.000 0.9856 0.01631 0.01083 -0.0504 0.0077 1.0000
7.250 1.0081 0.01733 0.01193 -0.0494 0.0073 1.0000
7.500 1.0310 0.01819 0.01286 -0.0487 0.0070 1.0000
7.750 1.0537 0.01903 0.01378 -0.0479 0.0066 1.0000
8.000 1.0751 0.02026 0.01512 -0.0470 0.0065 1.0000
8.250 1.0956 0.02169 0.01667 -0.0459 0.0063 1.0000
8.500 1.1145 0.02353 0.01870 -0.0447 0.0062 1.0000
8.750 1.1311 0.02584 0.02122 -0.0433 0.0061 1.0000
9.000 1.1435 0.02902 0.02469 -0.0415 0.0060 1.0000
9.250 1.1489 0.03332 0.02941 -0.0392 0.0059 1.0000
9.500 1.1433 0.03902 0.03559 -0.0361 0.0058 1.0000
9.750 1.1403 0.04310 0.03999 -0.0335 0.0058 1.0000
10.000 1.1394 0.04606 0.04316 -0.0313 0.0058 1.0000
10.250 1.1303 0.04923 0.04655 -0.0285 0.0059 1.0000
10.500 1.1227 0.05107 0.04851 -0.0254 0.0059 1.0000
10.750 0.9061 0.07024 0.06848 -0.0305 0.0090 1.0000
11.000 0.8853 0.07842 0.07676 -0.0355 0.0090 1.0000
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Polar data table (+)
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