NASA/AMES A-02 AIRFOIL (ames02-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/AMES A-02 AIRFOIL (ames02-il) Reynolds number: 50,000 Max Cl/Cd: 22.8 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ames02-il-50000-n5.txt Download as CSV file: xf-ames02-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6867 0.11430 0.10710 0.0227 1.0000 0.0572
-9.250 -0.6828 0.10986 0.10269 0.0214 1.0000 0.0553
-9.000 -0.6925 0.10213 0.09500 0.0147 1.0000 0.0519
-8.750 -0.6905 0.09746 0.09036 0.0125 1.0000 0.0512
-8.500 -0.6922 0.09185 0.08478 0.0084 1.0000 0.0505
-8.250 -0.6978 0.08580 0.07873 0.0035 1.0000 0.0497
-8.000 -0.7026 0.07966 0.07251 -0.0007 1.0000 0.0489
-7.750 -0.7061 0.07361 0.06631 -0.0042 1.0000 0.0484
-7.500 -0.7056 0.06805 0.06052 -0.0067 1.0000 0.0483
-7.250 -0.7004 0.06304 0.05523 -0.0083 1.0000 0.0485
-7.000 -0.6918 0.05823 0.05008 -0.0096 1.0000 0.0489
-6.750 -0.6799 0.05358 0.04500 -0.0104 1.0000 0.0491
-6.500 -0.6648 0.04912 0.04006 -0.0109 1.0000 0.0490
-6.250 -0.6465 0.04512 0.03555 -0.0111 1.0000 0.0492
-6.000 -0.6257 0.04152 0.03143 -0.0111 1.0000 0.0500
-5.750 -0.6029 0.03813 0.02732 -0.0109 1.0000 0.0519
-5.500 -0.5789 0.03597 0.02501 -0.0109 1.0000 0.0544
-5.250 -0.5531 0.03345 0.02204 -0.0106 1.0000 0.0565
-5.000 -0.5266 0.03121 0.01947 -0.0102 1.0000 0.0586
-4.750 -0.5001 0.02949 0.01757 -0.0099 1.0000 0.0628
-4.500 -0.4735 0.02783 0.01579 -0.0095 1.0000 0.0668
-4.250 -0.4465 0.02632 0.01414 -0.0089 1.0000 0.0721
-3.750 -0.3941 0.02382 0.01152 -0.0078 1.0000 0.0880
-3.500 -0.3683 0.02263 0.01039 -0.0074 1.0000 0.1000
-3.250 -0.3420 0.02148 0.00927 -0.0072 1.0000 0.1200
-3.000 -0.3171 0.02010 0.00820 -0.0069 1.0000 0.1596
-2.750 -0.2963 0.01785 0.00723 -0.0066 1.0000 0.3456
-2.500 -0.2833 0.01648 0.00728 -0.0023 1.0000 0.6476
-2.250 -0.2654 0.01611 0.00727 0.0020 1.0000 0.7871
-2.000 -0.2229 0.01604 0.00728 0.0024 1.0000 0.9163
-1.750 -0.1332 0.01609 0.00689 -0.0084 1.0000 0.9964
-1.500 -0.1095 0.01579 0.00642 -0.0087 1.0000 1.0000
-1.250 -0.0904 0.01554 0.00605 -0.0079 1.0000 1.0000
-1.000 -0.0714 0.01537 0.00574 -0.0070 1.0000 1.0000
-0.750 -0.0525 0.01526 0.00552 -0.0060 1.0000 1.0000
-0.500 -0.0336 0.01521 0.00538 -0.0049 1.0000 1.0000
-0.250 -0.0148 0.01521 0.00529 -0.0038 1.0000 1.0000
0.000 0.0041 0.01525 0.00527 -0.0026 1.0000 1.0000
0.250 0.0231 0.01534 0.00530 -0.0015 1.0000 1.0000
0.500 0.0426 0.01546 0.00539 -0.0004 1.0000 1.0000
0.750 0.0625 0.01562 0.00553 0.0005 1.0000 1.0000
1.000 0.0827 0.01581 0.00573 0.0013 1.0000 1.0000
1.250 0.1034 0.01605 0.00598 0.0020 1.0000 1.0000
1.500 0.1365 0.01632 0.00630 0.0003 0.9926 1.0000
1.750 0.2047 0.01648 0.00661 -0.0076 0.9631 1.0000
2.000 0.2587 0.01657 0.00686 -0.0122 0.9275 1.0000
2.250 0.2979 0.01664 0.00705 -0.0133 0.8852 1.0000
2.500 0.3250 0.01669 0.00717 -0.0118 0.8353 1.0000
2.750 0.3480 0.01672 0.00721 -0.0093 0.7759 1.0000
3.000 0.3688 0.01679 0.00717 -0.0061 0.6957 1.0000
3.250 0.3876 0.01710 0.00706 -0.0025 0.5790 1.0000
3.500 0.4064 0.01795 0.00718 0.0002 0.4427 1.0000
3.750 0.4282 0.01909 0.00766 0.0013 0.3378 1.0000
4.000 0.4518 0.02020 0.00833 0.0017 0.2714 1.0000
4.250 0.4764 0.02122 0.00910 0.0020 0.2266 1.0000
4.500 0.5019 0.02225 0.00998 0.0022 0.1942 1.0000
4.750 0.5275 0.02326 0.01090 0.0025 0.1693 1.0000
5.000 0.5531 0.02431 0.01185 0.0029 0.1505 1.0000
5.250 0.5790 0.02539 0.01295 0.0033 0.1346 1.0000
5.500 0.6047 0.02655 0.01415 0.0037 0.1218 1.0000
5.750 0.6303 0.02778 0.01539 0.0040 0.1113 1.0000
6.000 0.6558 0.02908 0.01675 0.0044 0.1022 1.0000
6.250 0.6816 0.03060 0.01851 0.0047 0.0943 1.0000
6.500 0.7068 0.03231 0.02042 0.0051 0.0878 1.0000
6.750 0.7312 0.03394 0.02210 0.0053 0.0826 1.0000
7.000 0.7553 0.03611 0.02468 0.0056 0.0775 1.0000
7.250 0.7780 0.03839 0.02728 0.0058 0.0734 1.0000
7.500 0.7994 0.04102 0.03030 0.0061 0.0699 1.0000
7.750 0.8191 0.04373 0.03334 0.0062 0.0669 1.0000
8.000 0.8347 0.04757 0.03777 0.0063 0.0644 1.0000
8.250 0.8501 0.05079 0.04132 0.0064 0.0625 1.0000
8.500 0.8603 0.05484 0.04579 0.0063 0.0609 1.0000
8.750 0.8597 0.06063 0.05217 0.0056 0.0596 1.0000
9.000 0.8548 0.06639 0.05833 0.0044 0.0588 1.0000
9.250 0.8435 0.07262 0.06485 0.0024 0.0586 1.0000
9.500 0.8249 0.07953 0.07195 -0.0010 0.0590 1.0000
9.750 0.8028 0.08731 0.07977 -0.0063 0.0596 1.0000
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Polar data table (+)
Polar graphs
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