USA 50 AIRFOIL (usa50-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 50 AIRFOIL (usa50-il) Reynolds number: 500,000 Max Cl/Cd: 73.32 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa50-il-500000-n5.txt Download as CSV file: xf-usa50-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 50 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4869 0.08428 0.08213 -0.0180 1.0000 0.0052
-7.750 -0.4855 0.08139 0.07927 -0.0192 1.0000 0.0059
-7.500 -0.5004 0.07772 0.07565 -0.0194 1.0000 0.0054
-7.250 -0.5006 0.07348 0.07143 -0.0221 1.0000 0.0055
-7.000 -0.4992 0.06916 0.06710 -0.0245 1.0000 0.0056
-6.750 -0.4979 0.06450 0.06241 -0.0267 1.0000 0.0054
-6.500 -0.4942 0.05996 0.05782 -0.0282 1.0000 0.0053
-6.250 -0.4891 0.05533 0.05311 -0.0291 1.0000 0.0052
-6.000 -0.4637 0.04886 0.04644 -0.0346 0.9973 0.0050
-5.750 -0.4368 0.04257 0.03989 -0.0388 0.9942 0.0049
-5.500 -0.4122 0.03704 0.03404 -0.0410 0.9907 0.0047
-5.250 -0.3858 0.03135 0.02797 -0.0425 0.9877 0.0045
-5.000 -0.3620 0.02603 0.02221 -0.0424 0.9840 0.0043
-4.750 -0.3381 0.02085 0.01646 -0.0416 0.9802 0.0042
-4.250 -0.2858 0.01475 0.00932 -0.0402 0.9732 0.0040
-4.000 -0.2580 0.01288 0.00711 -0.0398 0.9693 0.0040
-3.750 -0.2282 0.01137 0.00535 -0.0400 0.9664 0.0042
-3.500 -0.2056 0.01042 0.00424 -0.0387 0.9596 0.0047
-3.250 -0.1762 0.00981 0.00353 -0.0389 0.9556 0.0060
-3.000 -0.1488 0.00970 0.00339 -0.0388 0.9497 0.0119
-2.750 -0.1205 0.00945 0.00311 -0.0392 0.9440 0.0189
-2.500 -0.0900 0.00911 0.00269 -0.0397 0.9389 0.0194
-2.250 -0.0594 0.00881 0.00231 -0.0402 0.9319 0.0193
-2.000 -0.0236 0.00855 0.00198 -0.0419 0.9262 0.0193
-1.750 0.0132 0.00834 0.00171 -0.0439 0.9186 0.0194
-1.500 0.0537 0.00815 0.00146 -0.0467 0.9110 0.0197
-1.250 0.0955 0.00799 0.00120 -0.0498 0.8991 0.0229
-1.000 0.1347 0.00778 0.00105 -0.0524 0.8763 0.0554
-0.750 0.1680 0.00772 0.00093 -0.0536 0.8396 0.0755
-0.500 0.1903 0.00715 0.00082 -0.0527 0.7894 0.2877
-0.250 0.2109 0.00704 0.00079 -0.0512 0.7367 0.3911
0.250 0.2481 0.00661 0.00083 -0.0474 0.6567 0.6422
0.500 0.3319 0.00613 0.00112 -0.0598 0.6129 0.9797
0.750 0.3743 0.00635 0.00119 -0.0632 0.5844 0.9943
1.000 0.4144 0.00649 0.00125 -0.0662 0.5634 1.0000
1.250 0.4372 0.00662 0.00129 -0.0651 0.5456 1.0000
1.500 0.4600 0.00676 0.00134 -0.0641 0.5259 1.0000
1.750 0.4830 0.00690 0.00141 -0.0631 0.5072 1.0000
2.000 0.5057 0.00707 0.00148 -0.0621 0.4810 1.0000
2.250 0.5280 0.00726 0.00155 -0.0610 0.4426 1.0000
2.500 0.5499 0.00750 0.00162 -0.0598 0.3954 1.0000
2.750 0.5706 0.00787 0.00183 -0.0585 0.3385 1.0000
3.000 0.5924 0.00820 0.00202 -0.0573 0.3005 1.0000
3.250 0.6142 0.00854 0.00222 -0.0562 0.2612 1.0000
3.500 0.6324 0.00924 0.00252 -0.0545 0.1683 1.0000
3.750 0.6440 0.01069 0.00319 -0.0518 0.0115 1.0000
4.000 0.6657 0.01113 0.00365 -0.0504 0.0034 1.0000
4.250 0.6879 0.01152 0.00415 -0.0492 0.0029 1.0000
4.500 0.7093 0.01201 0.00476 -0.0478 0.0027 1.0000
4.750 0.7288 0.01273 0.00561 -0.0459 0.0025 1.0000
5.000 0.7472 0.01356 0.00655 -0.0439 0.0024 1.0000
5.250 0.7647 0.01451 0.00760 -0.0417 0.0024 1.0000
5.500 0.7821 0.01556 0.00874 -0.0395 0.0024 1.0000
5.750 0.7994 0.01684 0.01025 -0.0372 0.0025 1.0000
6.000 0.8179 0.01830 0.01186 -0.0352 0.0025 1.0000
6.250 0.8375 0.01980 0.01352 -0.0334 0.0025 1.0000
6.500 0.8569 0.02171 0.01565 -0.0315 0.0026 1.0000
6.750 0.8752 0.02372 0.01793 -0.0296 0.0027 1.0000
7.000 0.8915 0.02608 0.02059 -0.0272 0.0028 1.0000
7.250 0.9058 0.02849 0.02331 -0.0248 0.0028 1.0000
7.500 0.9164 0.03137 0.02653 -0.0219 0.0029 1.0000
7.750 0.9253 0.03418 0.02966 -0.0189 0.0030 1.0000
8.000 0.9305 0.03728 0.03308 -0.0158 0.0030 1.0000
8.250 0.9293 0.04111 0.03725 -0.0122 0.0032 1.0000
8.500 0.9265 0.04459 0.04100 -0.0089 0.0033 1.0000
10.000 0.8649 0.06264 0.05997 0.0051 0.0037 1.0000
10.250 0.8354 0.06959 0.06706 0.0012 0.0036 1.0000
10.500 0.8330 0.07385 0.07143 -0.0020 0.0037 1.0000
10.750 0.8108 0.08314 0.08083 -0.0095 0.0036 1.0000
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