NASA/AMES A-01 AIRFOIL (ames01-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/AMES A-01 AIRFOIL (ames01-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.47 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ames01-il-1000000-n5.txt Download as CSV file: xf-ames01-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -1.3252 0.05356 0.05083 -0.0221 1.0000 0.0036
-15.750 -1.3570 0.04621 0.04323 -0.0258 1.0000 0.0036
-15.500 -1.3739 0.04194 0.03876 -0.0259 1.0000 0.0036
-15.250 -1.3855 0.03876 0.03541 -0.0245 1.0000 0.0036
-15.000 -1.3920 0.03635 0.03283 -0.0222 1.0000 0.0036
-14.750 -1.3954 0.03437 0.03070 -0.0192 1.0000 0.0036
-14.500 -1.3909 0.03259 0.02878 -0.0171 1.0000 0.0037
-14.250 -1.3819 0.03095 0.02700 -0.0155 1.0000 0.0037
-14.000 -1.3696 0.02949 0.02539 -0.0142 1.0000 0.0038
-13.750 -1.3551 0.02816 0.02393 -0.0130 0.9829 0.0039
-13.500 -1.3414 0.02704 0.02267 -0.0114 0.9636 0.0039
-13.250 -1.3265 0.02600 0.02149 -0.0098 0.9548 0.0040
-13.000 -1.3101 0.02502 0.02038 -0.0083 0.9485 0.0040
-12.750 -1.2925 0.02400 0.01924 -0.0071 0.9438 0.0042
-12.500 -1.2735 0.02305 0.01819 -0.0061 0.9395 0.0043
-12.250 -1.2540 0.02216 0.01719 -0.0050 0.9352 0.0045
-12.000 -1.2338 0.02134 0.01625 -0.0040 0.9315 0.0047
-11.750 -1.2121 0.02055 0.01537 -0.0033 0.9280 0.0049
-11.500 -1.1899 0.01982 0.01456 -0.0026 0.9246 0.0051
-11.250 -1.1674 0.01915 0.01381 -0.0018 0.9215 0.0054
-11.000 -1.1446 0.01852 0.01309 -0.0011 0.9185 0.0057
-10.750 -1.1210 0.01789 0.01240 -0.0006 0.9156 0.0062
-10.500 -1.0968 0.01731 0.01175 -0.0001 0.9125 0.0067
-10.250 -1.0723 0.01679 0.01116 0.0004 0.9096 0.0073
-10.000 -1.0476 0.01631 0.01062 0.0008 0.9068 0.0076
-9.750 -1.0229 0.01585 0.01010 0.0013 0.9041 0.0080
-9.500 -0.9975 0.01538 0.00959 0.0017 0.9014 0.0085
-9.250 -0.9716 0.01496 0.00913 0.0020 0.8987 0.0090
-9.000 -0.9456 0.01456 0.00867 0.0022 0.8958 0.0094
-8.750 -0.9196 0.01419 0.00825 0.0025 0.8929 0.0099
-8.500 -0.8934 0.01384 0.00786 0.0029 0.8903 0.0102
-8.250 -0.8672 0.01350 0.00747 0.0031 0.8879 0.0106
-8.000 -0.8404 0.01314 0.00710 0.0033 0.8852 0.0112
-7.750 -0.8134 0.01282 0.00675 0.0034 0.8822 0.0119
-7.500 -0.7865 0.01252 0.00642 0.0036 0.8794 0.0125
-7.250 -0.7595 0.01223 0.00610 0.0038 0.8766 0.0129
-7.000 -0.7325 0.01196 0.00580 0.0040 0.8740 0.0136
-6.750 -0.7051 0.01168 0.00552 0.0041 0.8714 0.0147
-6.500 -0.6774 0.01143 0.00526 0.0041 0.8684 0.0157
-6.250 -0.6497 0.01119 0.00500 0.0041 0.8654 0.0166
-6.000 -0.6221 0.01096 0.00475 0.0042 0.8624 0.0175
-5.750 -0.5945 0.01073 0.00451 0.0043 0.8596 0.0185
-5.500 -0.5666 0.01052 0.00429 0.0044 0.8568 0.0196
-5.250 -0.5384 0.01031 0.00408 0.0043 0.8524 0.0206
-5.000 -0.5105 0.01012 0.00387 0.0044 0.8472 0.0216
-4.750 -0.4827 0.00992 0.00366 0.0045 0.8421 0.0232
-4.500 -0.4544 0.00974 0.00348 0.0045 0.8355 0.0249
-4.250 -0.4264 0.00957 0.00329 0.0045 0.8289 0.0260
-4.000 -0.3979 0.00942 0.00312 0.0045 0.8225 0.0271
-3.750 -0.3697 0.00925 0.00295 0.0045 0.8144 0.0295
-3.500 -0.3412 0.00910 0.00280 0.0045 0.8055 0.0318
-3.250 -0.3128 0.00900 0.00267 0.0044 0.7960 0.0340
-3.000 -0.2842 0.00884 0.00253 0.0044 0.7854 0.0378
-2.750 -0.2556 0.00872 0.00239 0.0043 0.7732 0.0406
-2.500 -0.2269 0.00863 0.00225 0.0042 0.7579 0.0424
-2.250 -0.1981 0.00856 0.00211 0.0041 0.7362 0.0439
-2.000 -0.1694 0.00850 0.00197 0.0040 0.7074 0.0478
-1.750 -0.1404 0.00847 0.00186 0.0038 0.6756 0.0518
-1.500 -0.1113 0.00850 0.00177 0.0035 0.6397 0.0548
-1.250 -0.0822 0.00855 0.00170 0.0032 0.5934 0.0622
-1.000 -0.0530 0.00866 0.00165 0.0028 0.5375 0.0720
-0.750 -0.0240 0.00882 0.00162 0.0024 0.4659 0.0905
-0.500 0.0045 0.00889 0.00160 0.0019 0.3943 0.1401
-0.250 0.0321 0.00865 0.00155 0.0016 0.3465 0.2515
0.000 0.0593 0.00833 0.00151 0.0014 0.3123 0.3798
0.250 0.0860 0.00793 0.00148 0.0013 0.2883 0.5219
0.500 0.1126 0.00757 0.00149 0.0014 0.2722 0.6480
0.750 0.1394 0.00734 0.00151 0.0016 0.2604 0.7349
1.000 0.1648 0.00710 0.00156 0.0022 0.2496 0.8274
1.250 0.1898 0.00698 0.00163 0.0031 0.2415 0.8952
1.500 0.2161 0.00701 0.00172 0.0038 0.2333 0.9424
1.750 0.2473 0.00710 0.00180 0.0033 0.2280 0.9651
2.000 0.2788 0.00720 0.00186 0.0025 0.2225 0.9737
2.250 0.3112 0.00733 0.00193 0.0015 0.2170 0.9804
2.500 0.3432 0.00742 0.00200 0.0007 0.2132 0.9850
2.750 0.3769 0.00753 0.00207 -0.0006 0.2082 0.9872
3.000 0.4104 0.00766 0.00215 -0.0019 0.2034 0.9893
3.250 0.4434 0.00777 0.00224 -0.0031 0.2003 0.9914
3.500 0.4758 0.00787 0.00233 -0.0041 0.1972 0.9936
3.750 0.5086 0.00799 0.00242 -0.0052 0.1929 0.9951
4.000 0.5421 0.00813 0.00252 -0.0066 0.1882 0.9963
4.250 0.5754 0.00824 0.00263 -0.0078 0.1853 0.9977
4.500 0.6085 0.00835 0.00274 -0.0090 0.1817 0.9991
4.750 0.6401 0.00849 0.00285 -0.0099 0.1767 1.0000
5.000 0.6660 0.00863 0.00296 -0.0096 0.1721 1.0000
5.250 0.6920 0.00873 0.00307 -0.0092 0.1687 1.0000
5.500 0.7179 0.00886 0.00318 -0.0089 0.1635 1.0000
5.750 0.7439 0.00902 0.00331 -0.0086 0.1573 1.0000
6.000 0.7700 0.00915 0.00344 -0.0083 0.1530 1.0000
6.250 0.7960 0.00932 0.00358 -0.0080 0.1469 1.0000
6.500 0.8221 0.00949 0.00374 -0.0078 0.1408 1.0000
6.750 0.8478 0.00973 0.00392 -0.0075 0.1307 1.0000
7.000 0.8738 0.00993 0.00411 -0.0073 0.1236 1.0000
7.250 0.8997 0.01017 0.00431 -0.0070 0.1155 1.0000
7.500 0.9253 0.01048 0.00456 -0.0068 0.1040 1.0000
7.750 0.9507 0.01083 0.00484 -0.0065 0.0914 1.0000
8.000 0.9759 0.01122 0.00516 -0.0063 0.0786 1.0000
8.250 1.0010 0.01162 0.00551 -0.0061 0.0679 1.0000
8.500 1.0261 0.01204 0.00589 -0.0058 0.0582 1.0000
8.750 1.0511 0.01246 0.00626 -0.0056 0.0501 1.0000
9.000 1.0761 0.01286 0.00664 -0.0054 0.0432 1.0000
9.250 1.1009 0.01331 0.00707 -0.0051 0.0369 1.0000
9.500 1.1253 0.01378 0.00751 -0.0048 0.0314 1.0000
9.750 1.1500 0.01419 0.00792 -0.0046 0.0277 1.0000
10.000 1.1741 0.01468 0.00840 -0.0043 0.0238 1.0000
10.250 1.1985 0.01510 0.00884 -0.0040 0.0218 1.0000
10.500 1.2223 0.01558 0.00933 -0.0036 0.0198 1.0000
10.750 1.2459 0.01606 0.00982 -0.0033 0.0181 1.0000
11.000 1.2696 0.01650 0.01030 -0.0029 0.0171 1.0000
11.250 1.2925 0.01700 0.01083 -0.0025 0.0159 1.0000
11.500 1.3147 0.01757 0.01142 -0.0020 0.0146 1.0000
11.750 1.3367 0.01811 0.01200 -0.0014 0.0137 1.0000
12.000 1.3588 0.01862 0.01255 -0.0009 0.0130 1.0000
12.250 1.3799 0.01918 0.01315 -0.0003 0.0122 1.0000
12.500 1.4001 0.01980 0.01381 0.0004 0.0114 1.0000
12.750 1.4192 0.02048 0.01453 0.0012 0.0107 1.0000
13.000 1.4378 0.02116 0.01526 0.0021 0.0102 1.0000
13.250 1.4561 0.02180 0.01597 0.0030 0.0100 1.0000
13.500 1.4730 0.02250 0.01673 0.0041 0.0097 1.0000
13.750 1.4878 0.02324 0.01754 0.0055 0.0094 1.0000
14.000 1.4987 0.02406 0.01842 0.0073 0.0091 1.0000
14.250 1.5088 0.02499 0.01942 0.0091 0.0088 1.0000
14.500 1.5184 0.02603 0.02052 0.0106 0.0086 1.0000
14.750 1.5271 0.02719 0.02176 0.0121 0.0083 1.0000
15.000 1.5347 0.02851 0.02315 0.0135 0.0081 1.0000
15.250 1.5408 0.02999 0.02471 0.0147 0.0078 1.0000
15.500 1.5450 0.03171 0.02652 0.0159 0.0076 1.0000
15.750 1.5494 0.03350 0.02840 0.0168 0.0075 1.0000
16.000 1.5528 0.03547 0.03047 0.0174 0.0074 1.0000
16.250 1.5542 0.03775 0.03286 0.0178 0.0073 1.0000
16.500 1.5537 0.04040 0.03562 0.0179 0.0072 1.0000
16.750 1.5502 0.04356 0.03890 0.0175 0.0071 1.0000
17.000 1.5435 0.04741 0.04287 0.0165 0.0071 1.0000
17.250 1.5325 0.05219 0.04780 0.0147 0.0070 1.0000
17.500 1.5151 0.05845 0.05423 0.0116 0.0070 1.0000
17.750 1.4872 0.06713 0.06310 0.0068 0.0070 1.0000
18.000 1.4425 0.07923 0.07545 0.0003 0.0071 1.0000
18.250 1.3840 0.09326 0.08970 -0.0066 0.0072 1.0000
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Polar data table (+)
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