NASA/AMES 63A108 MOD C AIRFOIL (a63a108c-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/AMES 63A108 MOD C AIRFOIL (a63a108c-il) Reynolds number: 50,000 Max Cl/Cd: 24.45 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-a63a108c-il-50000.txt Download as CSV file: xf-a63a108c-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/AMES 63A108 MOD C 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.6237 0.09716 0.09053 0.0416 1.0000 0.3510
-7.000 -0.6211 0.09426 0.08768 0.0426 1.0000 0.3754
-6.750 -0.6204 0.09114 0.08465 0.0438 1.0000 0.4005
-6.500 -0.5981 0.08728 0.08078 0.0461 1.0000 0.4279
-6.250 -0.5978 0.08444 0.07801 0.0478 1.0000 0.4566
-5.750 -0.6169 0.05190 0.04349 -0.0105 1.0000 0.1475
-5.500 -0.5949 0.04717 0.03860 -0.0110 1.0000 0.1416
-5.250 -0.5698 0.04245 0.03299 -0.0120 1.0000 0.1317
-5.000 -0.5443 0.03861 0.02875 -0.0121 1.0000 0.1279
-4.750 -0.5172 0.03535 0.02497 -0.0121 1.0000 0.1272
-4.500 -0.4894 0.03269 0.02183 -0.0119 1.0000 0.1304
-4.250 -0.4602 0.03029 0.01888 -0.0115 1.0000 0.1332
-4.000 -0.4326 0.02797 0.01656 -0.0112 1.0000 0.1411
-3.750 -0.4036 0.02598 0.01435 -0.0106 1.0000 0.1508
-3.500 -0.3754 0.02418 0.01257 -0.0100 1.0000 0.1663
-3.250 -0.3478 0.02243 0.01099 -0.0092 1.0000 0.1911
-3.000 -0.3212 0.02047 0.00937 -0.0084 1.0000 0.2415
-2.750 -0.3184 0.01656 0.00861 -0.0011 1.0000 0.6929
-2.500 -0.1880 0.01757 0.00895 -0.0095 1.0000 1.0000
-2.250 -0.1682 0.01699 0.00814 -0.0097 1.0000 1.0000
-2.000 -0.1484 0.01650 0.00746 -0.0096 1.0000 1.0000
-1.750 -0.1288 0.01610 0.00689 -0.0093 1.0000 1.0000
-1.500 -0.1096 0.01579 0.00643 -0.0087 1.0000 1.0000
-1.250 -0.0906 0.01555 0.00604 -0.0079 1.0000 1.0000
-1.000 -0.0715 0.01537 0.00575 -0.0070 1.0000 1.0000
-0.750 -0.0526 0.01526 0.00553 -0.0060 1.0000 1.0000
-0.500 -0.0337 0.01521 0.00538 -0.0049 1.0000 1.0000
-0.250 -0.0149 0.01521 0.00529 -0.0038 1.0000 1.0000
0.000 0.0040 0.01525 0.00527 -0.0026 1.0000 1.0000
0.250 0.0230 0.01534 0.00530 -0.0014 1.0000 1.0000
0.500 0.0425 0.01546 0.00539 -0.0004 1.0000 1.0000
0.750 0.0624 0.01562 0.00553 0.0006 1.0000 1.0000
1.000 0.0826 0.01581 0.00572 0.0014 1.0000 1.0000
1.250 0.1032 0.01605 0.00598 0.0021 1.0000 1.0000
1.500 0.1241 0.01633 0.00630 0.0026 1.0000 1.0000
1.750 0.1452 0.01666 0.00669 0.0030 1.0000 1.0000
2.000 0.1662 0.01705 0.00716 0.0033 1.0000 1.0000
2.250 0.1870 0.01751 0.00772 0.0035 1.0000 1.0000
2.500 0.2074 0.01806 0.00839 0.0034 1.0000 1.0000
2.750 0.2271 0.01873 0.00923 0.0032 1.0000 1.0000
3.000 0.3686 0.01876 0.01004 -0.0172 0.9285 1.0000
3.250 0.4203 0.01799 0.00965 -0.0159 0.8238 1.0000
3.500 0.4296 0.01757 0.00891 -0.0066 0.6744 1.0000
3.750 0.4391 0.01888 0.00880 0.0003 0.4758 1.0000
4.000 0.4601 0.02076 0.00977 0.0022 0.3711 1.0000
4.250 0.4854 0.02241 0.01107 0.0031 0.3102 1.0000
4.500 0.5117 0.02402 0.01249 0.0038 0.2693 1.0000
4.750 0.5379 0.02574 0.01398 0.0045 0.2403 1.0000
5.000 0.5653 0.02749 0.01588 0.0048 0.2169 1.0000
5.250 0.5923 0.02943 0.01797 0.0052 0.1989 1.0000
5.500 0.6189 0.03159 0.02027 0.0054 0.1847 1.0000
5.750 0.6447 0.03389 0.02256 0.0057 0.1731 1.0000
6.000 0.6709 0.03672 0.02608 0.0056 0.1644 1.0000
6.250 0.6951 0.03952 0.02885 0.0058 0.1571 1.0000
6.500 0.7175 0.04339 0.03358 0.0054 0.1532 1.0000
6.750 0.7373 0.04785 0.03863 0.0048 0.1517 1.0000
7.000 0.7535 0.05289 0.04419 0.0038 0.1520 1.0000
7.250 0.7667 0.05833 0.05003 0.0026 0.1539 1.0000
7.500 0.7824 0.06354 0.05542 0.0020 0.1582 1.0000
7.750 0.6941 0.09751 0.09035 -0.0464 0.3886 1.0000
8.000 0.7046 0.10145 0.09427 -0.0453 0.3702 1.0000
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Polar data table (+)
Polar graphs
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