NASA/AMES A-01 AIRFOIL (ames01-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/AMES A-01 AIRFOIL (ames01-il) Reynolds number: 50,000 Max Cl/Cd: 27.77 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ames01-il-50000-n5.txt Download as CSV file: xf-ames01-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/AMES A-01 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5952 0.11733 0.11032 -0.0009 1.0000 0.0676
-10.250 -0.5867 0.11321 0.10620 -0.0010 1.0000 0.0668
-10.000 -0.5853 0.10839 0.10141 -0.0032 1.0000 0.0665
-9.750 -0.5856 0.10332 0.09638 -0.0061 1.0000 0.0662
-9.500 -0.5872 0.09795 0.09104 -0.0095 1.0000 0.0659
-9.250 -0.5902 0.09222 0.08533 -0.0136 1.0000 0.0653
-9.000 -0.5969 0.08631 0.07944 -0.0181 1.0000 0.0647
-8.750 -0.6067 0.08115 0.07424 -0.0206 1.0000 0.0640
-8.500 -0.6146 0.07604 0.06905 -0.0227 1.0000 0.0634
-8.250 -0.6203 0.07105 0.06392 -0.0241 1.0000 0.0628
-8.000 -0.6234 0.06624 0.05890 -0.0249 1.0000 0.0623
-7.750 -0.6233 0.06166 0.05406 -0.0252 1.0000 0.0620
-7.500 -0.6199 0.05740 0.04947 -0.0250 1.0000 0.0620
-7.250 -0.6134 0.05358 0.04528 -0.0244 1.0000 0.0631
-7.000 -0.6048 0.05005 0.04130 -0.0234 1.0000 0.0647
-6.750 -0.5938 0.04679 0.03754 -0.0222 1.0000 0.0661
-6.500 -0.5807 0.04381 0.03407 -0.0207 1.0000 0.0670
-6.250 -0.5660 0.04117 0.03090 -0.0191 1.0000 0.0677
-6.000 -0.5505 0.03873 0.02834 -0.0178 1.0000 0.0697
-5.750 -0.5340 0.03703 0.02655 -0.0164 1.0000 0.0726
-5.500 -0.5171 0.03529 0.02455 -0.0147 1.0000 0.0754
-5.250 -0.4987 0.03348 0.02241 -0.0131 1.0000 0.0774
-5.000 -0.4790 0.03185 0.02044 -0.0115 1.0000 0.0797
-4.750 -0.4589 0.03043 0.01874 -0.0101 1.0000 0.0834
-4.500 -0.4387 0.02918 0.01749 -0.0089 1.0000 0.0876
-4.250 -0.4168 0.02801 0.01619 -0.0077 1.0000 0.0912
-4.000 -0.3942 0.02704 0.01501 -0.0065 1.0000 0.0959
-3.750 -0.3727 0.02605 0.01408 -0.0054 1.0000 0.1021
-3.500 -0.3505 0.02527 0.01319 -0.0043 1.0000 0.1084
-3.250 -0.3284 0.02448 0.01235 -0.0033 1.0000 0.1146
-3.000 -0.3068 0.02385 0.01164 -0.0023 1.0000 0.1256
-2.750 -0.2859 0.02314 0.01097 -0.0013 1.0000 0.1380
-2.500 -0.2654 0.02246 0.01034 -0.0003 1.0000 0.1550
-2.250 -0.2450 0.02144 0.00978 0.0005 1.0000 0.2079
-2.000 -0.2323 0.01923 0.00962 0.0031 1.0000 0.5759
-1.750 -0.0846 0.01954 0.01049 -0.0148 1.0000 1.0000
-1.500 -0.0792 0.01951 0.01029 -0.0117 1.0000 1.0000
-1.250 -0.0718 0.01953 0.01013 -0.0089 1.0000 1.0000
-1.000 -0.0625 0.01960 0.01004 -0.0063 1.0000 1.0000
-0.750 -0.0520 0.01970 0.00999 -0.0039 1.0000 1.0000
-0.500 0.0080 0.01993 0.00999 -0.0108 0.9848 1.0000
-0.250 0.0909 0.01999 0.00987 -0.0215 0.9614 1.0000
0.000 0.1593 0.01988 0.00964 -0.0290 0.9380 1.0000
0.250 0.2040 0.01984 0.00953 -0.0320 0.9192 1.0000
0.500 0.2365 0.01984 0.00948 -0.0326 0.9013 1.0000
0.750 0.2633 0.01983 0.00944 -0.0320 0.8814 1.0000
1.000 0.2898 0.01976 0.00935 -0.0311 0.8607 1.0000
1.250 0.3127 0.01967 0.00925 -0.0295 0.8376 1.0000
1.500 0.3357 0.01952 0.00909 -0.0277 0.8130 1.0000
1.750 0.3567 0.01937 0.00894 -0.0256 0.7829 1.0000
2.000 0.3771 0.01923 0.00880 -0.0233 0.7454 1.0000
2.250 0.3985 0.01904 0.00856 -0.0210 0.6988 1.0000
2.500 0.4203 0.01886 0.00817 -0.0184 0.6359 1.0000
2.750 0.4409 0.01892 0.00780 -0.0155 0.5589 1.0000
3.000 0.4604 0.01939 0.00774 -0.0132 0.4924 1.0000
3.250 0.4805 0.02002 0.00796 -0.0116 0.4466 1.0000
3.500 0.5018 0.02065 0.00833 -0.0104 0.4155 1.0000
3.750 0.5243 0.02127 0.00876 -0.0095 0.3924 1.0000
4.000 0.5476 0.02188 0.00922 -0.0087 0.3749 1.0000
4.250 0.5715 0.02247 0.00973 -0.0080 0.3600 1.0000
4.500 0.5959 0.02307 0.01027 -0.0075 0.3472 1.0000
4.750 0.6208 0.02368 0.01083 -0.0069 0.3365 1.0000
5.000 0.6460 0.02430 0.01143 -0.0064 0.3262 1.0000
5.250 0.6713 0.02494 0.01214 -0.0060 0.3164 1.0000
5.500 0.6968 0.02563 0.01278 -0.0056 0.3084 1.0000
5.750 0.7219 0.02632 0.01362 -0.0052 0.2995 1.0000
6.000 0.7472 0.02708 0.01439 -0.0048 0.2919 1.0000
6.250 0.7719 0.02786 0.01532 -0.0044 0.2835 1.0000
6.500 0.7969 0.02870 0.01619 -0.0040 0.2767 1.0000
6.750 0.8209 0.02958 0.01729 -0.0036 0.2684 1.0000
7.000 0.8453 0.03047 0.01823 -0.0032 0.2613 1.0000
7.250 0.8684 0.03146 0.01947 -0.0027 0.2531 1.0000
7.500 0.8919 0.03240 0.02047 -0.0022 0.2456 1.0000
7.750 0.9137 0.03345 0.02181 -0.0016 0.2370 1.0000
8.000 0.9358 0.03447 0.02297 -0.0010 0.2289 1.0000
8.250 0.9569 0.03548 0.02418 -0.0004 0.2200 1.0000
8.500 0.9764 0.03664 0.02560 0.0004 0.2108 1.0000
8.750 0.9983 0.03736 0.02637 0.0011 0.2023 1.0000
9.000 1.0141 0.03864 0.02803 0.0022 0.1914 1.0000
9.250 1.0311 0.03971 0.02932 0.0032 0.1816 1.0000
9.500 1.0505 0.04016 0.02977 0.0042 0.1722 1.0000
9.750 1.0628 0.04152 0.03151 0.0055 0.1612 1.0000
10.000 1.0745 0.04274 0.03303 0.0069 0.1506 1.0000
10.250 1.0867 0.04374 0.03419 0.0083 0.1409 1.0000
10.500 1.1004 0.04418 0.03462 0.0098 0.1317 1.0000
10.750 1.1037 0.04625 0.03703 0.0115 0.1220 1.0000
11.000 1.1080 0.04798 0.03892 0.0132 0.1141 1.0000
11.250 1.1128 0.04926 0.04024 0.0149 0.1070 1.0000
11.500 1.1057 0.05208 0.04330 0.0169 0.1016 1.0000
11.750 1.0983 0.05474 0.04616 0.0186 0.0971 1.0000
12.000 1.0987 0.05653 0.04788 0.0198 0.0928 1.0000
12.250 1.0768 0.06161 0.05331 0.0199 0.0904 1.0000
12.500 1.0513 0.06773 0.05970 0.0184 0.0889 1.0000
12.750 1.0139 0.07678 0.06896 0.0140 0.0892 1.0000
13.000 0.9565 0.09181 0.08415 0.0049 0.0912 1.0000
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Polar data table (+)
Polar graphs
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