NASA/AMES A-02 AIRFOIL (ames02-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/AMES A-02 AIRFOIL (ames02-il) Reynolds number: 200,000 Max Cl/Cd: 37.34 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ames02-il-200000.txt Download as CSV file: xf-ames02-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/AMES A-02 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6981 0.09587 0.09243 0.0223 1.0000 0.0497
-8.250 -0.7058 0.08920 0.08580 0.0155 1.0000 0.0510
-8.000 -0.7408 0.07609 0.07235 -0.0025 1.0000 0.0520
-7.750 -0.7255 0.07315 0.06956 -0.0009 1.0000 0.0525
-7.500 -0.7143 0.07041 0.06682 -0.0005 1.0000 0.0535
-7.250 -0.7072 0.06596 0.06226 -0.0025 1.0000 0.0555
-7.000 -0.7054 0.05887 0.05479 -0.0063 1.0000 0.0586
-6.750 -0.6895 0.05603 0.05194 -0.0064 1.0000 0.0602
-6.500 -0.6784 0.05073 0.04619 -0.0080 1.0000 0.0651
-6.250 -0.6592 0.04802 0.04348 -0.0081 1.0000 0.0673
-6.000 -0.6418 0.04404 0.03914 -0.0088 1.0000 0.0730
-5.750 -0.6207 0.03115 0.02429 -0.0071 1.0000 0.0419
-5.500 -0.5960 0.02831 0.02134 -0.0072 1.0000 0.0426
-5.250 -0.5692 0.02530 0.01796 -0.0068 1.0000 0.0404
-5.000 -0.5417 0.02259 0.01482 -0.0063 1.0000 0.0395
-4.750 -0.5137 0.02067 0.01262 -0.0060 1.0000 0.0399
-4.500 -0.4854 0.01923 0.01089 -0.0057 1.0000 0.0414
-4.250 -0.4577 0.01804 0.00972 -0.0057 1.0000 0.0441
-4.000 -0.4294 0.01693 0.00848 -0.0055 1.0000 0.0463
-3.750 -0.4019 0.01579 0.00742 -0.0054 1.0000 0.0489
-3.500 -0.3742 0.01490 0.00656 -0.0053 1.0000 0.0535
-3.250 -0.3466 0.01406 0.00579 -0.0053 1.0000 0.0594
-3.000 -0.3189 0.01327 0.00510 -0.0053 1.0000 0.0676
-2.750 -0.2911 0.01250 0.00444 -0.0054 1.0000 0.0828
-2.500 -0.2637 0.01144 0.00375 -0.0056 1.0000 0.1387
-2.250 -0.2430 0.00915 0.00334 -0.0054 1.0000 0.5400
-2.000 -0.2207 0.00858 0.00338 -0.0039 1.0000 0.6930
-1.750 -0.1980 0.00834 0.00337 -0.0022 1.0000 0.7708
-1.500 -0.1771 0.00816 0.00337 -0.0001 1.0000 0.8297
-1.250 -0.1573 0.00807 0.00342 0.0024 1.0000 0.8856
-1.000 -0.1267 0.00809 0.00349 0.0026 1.0000 0.9451
-0.750 -0.0702 0.00817 0.00352 -0.0029 1.0000 0.9894
-0.500 -0.0384 0.00816 0.00345 -0.0044 1.0000 1.0000
-0.250 -0.0252 0.00823 0.00344 -0.0025 1.0000 1.0000
0.000 -0.0018 0.00833 0.00349 -0.0022 0.9986 1.0000
0.250 0.0514 0.00827 0.00340 -0.0075 0.9883 1.0000
0.500 0.1008 0.00823 0.00333 -0.0119 0.9747 1.0000
0.750 0.1397 0.00823 0.00332 -0.0138 0.9559 1.0000
1.000 0.1666 0.00830 0.00337 -0.0130 0.9342 1.0000
1.250 0.1874 0.00837 0.00341 -0.0109 0.9107 1.0000
1.500 0.2071 0.00842 0.00342 -0.0084 0.8869 1.0000
1.750 0.2282 0.00844 0.00340 -0.0062 0.8605 1.0000
2.000 0.2497 0.00845 0.00335 -0.0041 0.8305 1.0000
2.250 0.2727 0.00846 0.00329 -0.0023 0.7918 1.0000
2.500 0.2960 0.00853 0.00321 -0.0006 0.7386 1.0000
2.750 0.3196 0.00876 0.00314 0.0010 0.6541 1.0000
3.000 0.3435 0.00939 0.00313 0.0022 0.5162 1.0000
3.250 0.3693 0.01033 0.00334 0.0022 0.3660 1.0000
3.500 0.3962 0.01117 0.00368 0.0020 0.2666 1.0000
3.750 0.4237 0.01185 0.00405 0.0017 0.2073 1.0000
4.000 0.4512 0.01251 0.00445 0.0015 0.1689 1.0000
4.250 0.4787 0.01311 0.00492 0.0014 0.1419 1.0000
4.500 0.5060 0.01378 0.00545 0.0014 0.1224 1.0000
4.750 0.5334 0.01439 0.00599 0.0014 0.1072 1.0000
5.000 0.5606 0.01504 0.00656 0.0014 0.0954 1.0000
5.250 0.5877 0.01574 0.00722 0.0014 0.0859 1.0000
5.500 0.6146 0.01647 0.00792 0.0015 0.0779 1.0000
5.750 0.6413 0.01727 0.00869 0.0016 0.0713 1.0000
6.000 0.6679 0.01816 0.00956 0.0018 0.0659 1.0000
6.250 0.6942 0.01908 0.01041 0.0019 0.0612 1.0000
6.500 0.7210 0.01996 0.01140 0.0021 0.0571 1.0000
6.750 0.7473 0.02120 0.01273 0.0023 0.0540 1.0000
7.000 0.7735 0.02219 0.01372 0.0025 0.0510 1.0000
7.250 0.7993 0.02365 0.01545 0.0028 0.0483 1.0000
7.500 0.8249 0.02499 0.01688 0.0030 0.0464 1.0000
7.750 0.8495 0.02693 0.01901 0.0032 0.0451 1.0000
8.000 0.8723 0.02930 0.02194 0.0037 0.0434 1.0000
8.250 0.8960 0.03072 0.02345 0.0039 0.0417 1.0000
8.500 0.9175 0.03311 0.02602 0.0042 0.0407 1.0000
8.750 0.9328 0.03719 0.03078 0.0049 0.0405 1.0000
9.000 0.9441 0.04185 0.03599 0.0055 0.0406 1.0000
9.250 0.9529 0.04665 0.04122 0.0060 0.0411 1.0000
9.500 0.7785 0.09488 0.09124 -0.0202 0.0735 1.0000
9.750 0.7689 0.10154 0.09785 -0.0255 0.0713 1.0000
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Polar data table (+)
Polar graphs
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