NASA/AMES A-02 AIRFOIL (ames02-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/AMES A-02 AIRFOIL (ames02-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.82 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ames02-il-1000000-n5.txt Download as CSV file: xf-ames02-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -1.2404 0.05249 0.05018 -0.0040 1.0000 0.0057
-13.250 -1.2699 0.04513 0.04256 -0.0086 1.0000 0.0056
-13.000 -1.2906 0.04094 0.03815 -0.0071 1.0000 0.0056
-12.750 -1.2960 0.03731 0.03427 -0.0061 1.0000 0.0057
-12.500 -1.2923 0.03440 0.03113 -0.0051 1.0000 0.0058
-12.250 -1.2823 0.03211 0.02863 -0.0042 1.0000 0.0058
-12.000 -1.2685 0.03018 0.02654 -0.0035 1.0000 0.0059
-11.750 -1.2519 0.02856 0.02476 -0.0028 1.0000 0.0060
-11.500 -1.2334 0.02715 0.02321 -0.0022 1.0000 0.0060
-11.250 -1.2136 0.02587 0.02178 -0.0017 1.0000 0.0061
-11.000 -1.1928 0.02466 0.02044 -0.0013 1.0000 0.0062
-10.750 -1.1711 0.02356 0.01920 -0.0009 1.0000 0.0063
-10.500 -1.1486 0.02252 0.01805 -0.0005 1.0000 0.0064
-10.250 -1.1255 0.02154 0.01694 -0.0001 1.0000 0.0065
-10.000 -1.1019 0.02059 0.01588 0.0002 1.0000 0.0067
-9.750 -1.0778 0.01971 0.01488 0.0004 1.0000 0.0068
-9.500 -1.0533 0.01886 0.01390 0.0007 1.0000 0.0070
-9.250 -1.0281 0.01810 0.01305 0.0009 1.0000 0.0071
-9.000 -1.0025 0.01743 0.01227 0.0011 1.0000 0.0073
-8.750 -0.9765 0.01683 0.01158 0.0012 1.0000 0.0075
-8.500 -0.9505 0.01615 0.01081 0.0013 1.0000 0.0076
-8.250 -0.9245 0.01543 0.01003 0.0014 1.0000 0.0079
-8.000 -0.8978 0.01489 0.00944 0.0015 1.0000 0.0081
-7.750 -0.8708 0.01439 0.00889 0.0015 1.0000 0.0083
-7.500 -0.8435 0.01393 0.00838 0.0015 1.0000 0.0085
-7.250 -0.8162 0.01346 0.00786 0.0016 1.0000 0.0087
-7.000 -0.7886 0.01301 0.00737 0.0015 1.0000 0.0090
-6.750 -0.7609 0.01258 0.00689 0.0015 1.0000 0.0093
-6.500 -0.7330 0.01217 0.00644 0.0014 1.0000 0.0095
-6.250 -0.7048 0.01181 0.00603 0.0013 1.0000 0.0097
-6.000 -0.6768 0.01133 0.00554 0.0012 1.0000 0.0101
-5.750 -0.6484 0.01098 0.00518 0.0011 1.0000 0.0105
-5.250 -0.5907 0.01046 0.00461 0.0007 0.9700 0.0115
-5.000 -0.5643 0.01027 0.00438 0.0012 0.9566 0.0120
-4.750 -0.5384 0.01002 0.00410 0.0017 0.9462 0.0127
-4.500 -0.5115 0.00981 0.00388 0.0020 0.9374 0.0133
-4.250 -0.4845 0.00961 0.00365 0.0024 0.9298 0.0140
-4.000 -0.4571 0.00941 0.00342 0.0026 0.9221 0.0148
-3.750 -0.4297 0.00922 0.00322 0.0028 0.9150 0.0158
-3.500 -0.4018 0.00905 0.00304 0.0030 0.9074 0.0170
-3.250 -0.3742 0.00888 0.00286 0.0032 0.9002 0.0188
-3.000 -0.3459 0.00871 0.00269 0.0032 0.8923 0.0210
-2.500 -0.2896 0.00842 0.00239 0.0034 0.8760 0.0275
-2.250 -0.2616 0.00828 0.00226 0.0035 0.8659 0.0330
-2.000 -0.2334 0.00814 0.00213 0.0036 0.8515 0.0419
-1.750 -0.2053 0.00800 0.00199 0.0037 0.8318 0.0539
-1.500 -0.1771 0.00786 0.00186 0.0037 0.8088 0.0739
-1.250 -0.1487 0.00767 0.00174 0.0037 0.7864 0.1091
-1.000 -0.1201 0.00741 0.00163 0.0035 0.7655 0.1660
-0.750 -0.0916 0.00715 0.00151 0.0033 0.7353 0.2397
-0.500 -0.0629 0.00684 0.00141 0.0030 0.7005 0.3366
-0.250 -0.0344 0.00647 0.00133 0.0027 0.6594 0.4621
0.000 -0.0056 0.00633 0.00130 0.0024 0.6054 0.5505
0.250 0.0231 0.00630 0.00131 0.0021 0.5410 0.6254
0.500 0.0520 0.00642 0.00134 0.0018 0.4698 0.6767
0.750 0.0807 0.00656 0.00139 0.0015 0.4004 0.7222
1.000 0.1091 0.00669 0.00145 0.0014 0.3366 0.7673
1.250 0.1376 0.00683 0.00151 0.0012 0.2841 0.7982
1.500 0.1661 0.00697 0.00156 0.0011 0.2426 0.8198
1.750 0.1942 0.00707 0.00162 0.0011 0.2090 0.8454
2.000 0.2213 0.00713 0.00169 0.0014 0.1812 0.8790
2.250 0.2466 0.00716 0.00175 0.0022 0.1576 0.9232
2.500 0.2749 0.00722 0.00178 0.0023 0.1361 0.9712
2.750 0.3075 0.00736 0.00183 0.0013 0.1177 1.0000
3.000 0.3364 0.00756 0.00194 0.0011 0.1020 1.0000
3.250 0.3653 0.00774 0.00205 0.0009 0.0895 1.0000
3.500 0.3942 0.00793 0.00217 0.0007 0.0783 1.0000
3.750 0.4230 0.00812 0.00230 0.0005 0.0689 1.0000
4.000 0.4518 0.00832 0.00244 0.0003 0.0606 1.0000
4.250 0.4805 0.00852 0.00260 0.0001 0.0533 1.0000
4.500 0.5092 0.00872 0.00276 0.0000 0.0473 1.0000
4.750 0.5379 0.00893 0.00293 -0.0002 0.0426 1.0000
5.000 0.5665 0.00914 0.00311 -0.0004 0.0387 1.0000
5.250 0.5950 0.00936 0.00331 -0.0005 0.0351 1.0000
5.500 0.6234 0.00958 0.00352 -0.0007 0.0318 1.0000
5.750 0.6518 0.00983 0.00374 -0.0008 0.0291 1.0000
6.000 0.6802 0.01006 0.00397 -0.0009 0.0269 1.0000
6.250 0.7084 0.01031 0.00422 -0.0010 0.0250 1.0000
6.500 0.7365 0.01059 0.00448 -0.0012 0.0231 1.0000
6.750 0.7646 0.01085 0.00476 -0.0013 0.0215 1.0000
7.000 0.7925 0.01116 0.00505 -0.0014 0.0201 1.0000
7.250 0.8204 0.01144 0.00536 -0.0015 0.0190 1.0000
7.500 0.8482 0.01175 0.00568 -0.0015 0.0180 1.0000
7.750 0.8757 0.01211 0.00604 -0.0016 0.0171 1.0000
8.000 0.9033 0.01243 0.00640 -0.0017 0.0164 1.0000
8.250 0.9307 0.01278 0.00678 -0.0017 0.0158 1.0000
8.500 0.9579 0.01316 0.00718 -0.0017 0.0151 1.0000
8.750 0.9848 0.01360 0.00764 -0.0017 0.0145 1.0000
9.000 1.0117 0.01398 0.00807 -0.0017 0.0141 1.0000
9.250 1.0385 0.01438 0.00851 -0.0017 0.0136 1.0000
9.500 1.0650 0.01482 0.00898 -0.0017 0.0132 1.0000
9.750 1.0913 0.01529 0.00949 -0.0017 0.0128 1.0000
10.000 1.1171 0.01584 0.01009 -0.0016 0.0124 1.0000
10.250 1.1427 0.01641 0.01071 -0.0015 0.0121 1.0000
10.500 1.1683 0.01692 0.01129 -0.0014 0.0119 1.0000
10.750 1.1937 0.01743 0.01187 -0.0012 0.0115 1.0000
11.000 1.2189 0.01794 0.01244 -0.0011 0.0111 1.0000
11.250 1.2439 0.01847 0.01302 -0.0010 0.0107 1.0000
11.500 1.2682 0.01909 0.01368 -0.0008 0.0104 1.0000
11.750 1.2915 0.01985 0.01450 -0.0005 0.0100 1.0000
12.000 1.3153 0.02048 0.01521 -0.0002 0.0098 1.0000
12.250 1.3384 0.02117 0.01599 0.0001 0.0096 1.0000
12.500 1.3610 0.02191 0.01683 0.0004 0.0094 1.0000
12.750 1.3831 0.02267 0.01768 0.0008 0.0092 1.0000
13.000 1.4046 0.02345 0.01854 0.0012 0.0090 1.0000
13.250 1.4255 0.02427 0.01945 0.0017 0.0088 1.0000
13.500 1.4456 0.02515 0.02041 0.0023 0.0086 1.0000
13.750 1.4646 0.02610 0.02144 0.0029 0.0084 1.0000
14.000 1.4821 0.02718 0.02262 0.0036 0.0082 1.0000
14.250 1.4976 0.02840 0.02394 0.0044 0.0081 1.0000
14.500 1.5108 0.02977 0.02542 0.0054 0.0079 1.0000
14.750 1.5235 0.03105 0.02682 0.0065 0.0079 1.0000
15.000 1.5332 0.03246 0.02836 0.0078 0.0078 1.0000
15.250 1.5371 0.03402 0.03004 0.0096 0.0077 1.0000
15.500 1.5347 0.03597 0.03213 0.0115 0.0076 1.0000
15.750 1.5306 0.03851 0.03481 0.0124 0.0076 1.0000
16.000 1.5240 0.04177 0.03822 0.0122 0.0075 1.0000
16.250 1.5135 0.04612 0.04274 0.0105 0.0075 1.0000
16.500 1.4931 0.05298 0.04981 0.0060 0.0075 1.0000
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