NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il) Reynolds number: 50,000 Max Cl/Cd: 27.54 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ames03-il-50000.txt Download as CSV file: xf-ames03-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/AMES A-03 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4972 0.09259 0.08667 0.0165 1.0000 0.3879
-7.250 -0.4958 0.08737 0.08155 0.0179 1.0000 0.4423
-6.500 -0.5858 0.06036 0.05375 -0.0222 1.0000 0.2004
-6.250 -0.5802 0.05328 0.04581 -0.0232 1.0000 0.1534
-6.000 -0.5713 0.04886 0.04071 -0.0220 1.0000 0.1391
-5.750 -0.5573 0.04523 0.03695 -0.0207 1.0000 0.1351
-5.500 -0.5428 0.04186 0.03311 -0.0193 1.0000 0.1314
-5.250 -0.5261 0.03911 0.02989 -0.0180 1.0000 0.1322
-5.000 -0.5070 0.03658 0.02692 -0.0167 1.0000 0.1338
-4.750 -0.4854 0.03414 0.02403 -0.0156 1.0000 0.1346
-4.500 -0.4622 0.03203 0.02144 -0.0144 1.0000 0.1375
-4.250 -0.4394 0.03012 0.01940 -0.0136 1.0000 0.1454
-4.000 -0.4143 0.02856 0.01747 -0.0125 1.0000 0.1539
-3.750 -0.3892 0.02697 0.01587 -0.0116 1.0000 0.1674
-3.500 -0.3633 0.02550 0.01449 -0.0107 1.0000 0.1876
-3.250 -0.1287 0.02212 0.01391 -0.0309 1.0000 1.0000
-3.000 -0.1299 0.02182 0.01343 -0.0278 1.0000 1.0000
-2.750 -0.1305 0.02156 0.01298 -0.0245 1.0000 1.0000
-2.500 -0.1303 0.02132 0.01255 -0.0212 1.0000 1.0000
-2.250 -0.1292 0.02109 0.01216 -0.0179 1.0000 1.0000
-2.000 -0.1271 0.02089 0.01180 -0.0146 1.0000 1.0000
-1.750 -0.1237 0.02071 0.01146 -0.0115 1.0000 1.0000
-1.500 -0.1185 0.02057 0.01116 -0.0085 1.0000 1.0000
-1.250 -0.1116 0.02046 0.01090 -0.0058 1.0000 1.0000
-1.000 -0.1021 0.02040 0.01067 -0.0034 1.0000 1.0000
-0.750 -0.0895 0.02041 0.01051 -0.0016 1.0000 1.0000
-0.500 -0.0741 0.02048 0.01043 -0.0003 1.0000 1.0000
-0.250 -0.0567 0.02060 0.01041 0.0007 1.0000 1.0000
0.000 -0.0379 0.02077 0.01045 0.0015 1.0000 1.0000
0.250 -0.0181 0.02099 0.01056 0.0020 1.0000 1.0000
0.500 0.0024 0.02124 0.01072 0.0024 1.0000 1.0000
0.750 0.0233 0.02154 0.01095 0.0028 1.0000 1.0000
1.000 0.0446 0.02187 0.01122 0.0030 1.0000 1.0000
1.250 0.0660 0.02225 0.01157 0.0031 1.0000 1.0000
1.500 0.0876 0.02267 0.01197 0.0032 1.0000 1.0000
1.750 0.1090 0.02314 0.01244 0.0031 1.0000 1.0000
2.000 0.1304 0.02367 0.01300 0.0030 1.0000 1.0000
2.250 0.1866 0.02480 0.01421 -0.0037 0.9858 1.0000
2.500 0.2817 0.02642 0.01604 -0.0167 0.9490 1.0000
2.750 0.3599 0.02724 0.01717 -0.0251 0.9054 1.0000
3.000 0.4470 0.02690 0.01723 -0.0321 0.8527 1.0000
3.250 0.4889 0.02535 0.01597 -0.0293 0.7946 1.0000
3.500 0.5137 0.02298 0.01375 -0.0229 0.7208 1.0000
3.750 0.5353 0.02103 0.01168 -0.0169 0.6248 1.0000
4.000 0.5559 0.02031 0.01029 -0.0117 0.5564 1.0000
4.250 0.5767 0.02094 0.01036 -0.0090 0.5106 1.0000
4.500 0.6003 0.02189 0.01100 -0.0077 0.4778 1.0000
4.750 0.6251 0.02288 0.01177 -0.0067 0.4534 1.0000
5.000 0.6511 0.02392 0.01277 -0.0063 0.4327 1.0000
5.250 0.6771 0.02501 0.01386 -0.0059 0.4142 1.0000
5.500 0.7033 0.02618 0.01505 -0.0056 0.3980 1.0000
5.750 0.7295 0.02743 0.01635 -0.0054 0.3826 1.0000
6.000 0.7555 0.02880 0.01784 -0.0053 0.3680 1.0000
6.250 0.7812 0.03029 0.01945 -0.0053 0.3540 1.0000
6.500 0.8064 0.03190 0.02121 -0.0052 0.3401 1.0000
6.750 0.8311 0.03365 0.02312 -0.0052 0.3268 1.0000
7.000 0.8549 0.03549 0.02515 -0.0051 0.3131 1.0000
7.250 0.8785 0.03746 0.02722 -0.0048 0.3001 1.0000
7.500 0.9010 0.03949 0.02942 -0.0045 0.2860 1.0000
7.750 0.9200 0.04205 0.03242 -0.0046 0.2729 1.0000
8.000 0.9374 0.04470 0.03540 -0.0043 0.2590 1.0000
8.250 0.9515 0.04796 0.03906 -0.0041 0.2471 1.0000
8.500 0.9645 0.05106 0.04244 -0.0036 0.2346 1.0000
8.750 0.9784 0.05398 0.04554 -0.0030 0.2222 1.0000
9.000 0.9942 0.05654 0.04819 -0.0021 0.2089 1.0000
9.250 0.9782 0.06257 0.05485 -0.0023 0.2035 1.0000
9.500 0.9892 0.06553 0.05789 -0.0013 0.1926 1.0000
9.750 0.9644 0.07233 0.06502 -0.0021 0.1916 1.0000
10.000 0.9367 0.07944 0.07228 -0.0038 0.1924 1.0000
10.250 0.9102 0.08657 0.07943 -0.0058 0.1936 1.0000
10.500 0.8882 0.09446 0.08735 -0.0091 0.1949 1.0000
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Polar data table (+)
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