NASA/AMES A-01 AIRFOIL (ames01-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/AMES A-01 AIRFOIL (ames01-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.07 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ames01-il-1000000.txt Download as CSV file: xf-ames01-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -1.2981 0.05463 0.05208 -0.0200 1.0000 0.0058
-15.500 -1.3229 0.04753 0.04476 -0.0245 1.0000 0.0057
-15.250 -1.3453 0.04232 0.03932 -0.0256 1.0000 0.0058
-15.000 -1.3603 0.03874 0.03556 -0.0244 1.0000 0.0058
-14.750 -1.3721 0.03589 0.03252 -0.0217 1.0000 0.0059
-14.500 -1.3780 0.03368 0.03014 -0.0186 1.0000 0.0060
-14.250 -1.3747 0.03162 0.02793 -0.0165 1.0000 0.0061
-14.000 -1.3654 0.02991 0.02606 -0.0149 1.0000 0.0063
-13.750 -1.3526 0.02840 0.02443 -0.0136 1.0000 0.0065
-13.500 -1.3371 0.02707 0.02299 -0.0126 1.0000 0.0067
-13.250 -1.3197 0.02587 0.02168 -0.0117 1.0000 0.0069
-13.000 -1.3009 0.02476 0.02045 -0.0109 1.0000 0.0072
-12.750 -1.2806 0.02373 0.01930 -0.0103 1.0000 0.0075
-12.500 -1.2591 0.02279 0.01824 -0.0098 1.0000 0.0077
-12.250 -1.2384 0.02161 0.01695 -0.0093 1.0000 0.0083
-12.000 -1.2150 0.02077 0.01606 -0.0091 1.0000 0.0087
-11.750 -1.1903 0.02006 0.01528 -0.0090 1.0000 0.0093
-11.250 -1.1417 0.01893 0.01396 -0.0083 0.9752 0.0101
-11.000 -1.1211 0.01826 0.01321 -0.0072 0.9680 0.0107
-10.750 -1.1000 0.01779 0.01268 -0.0060 0.9618 0.0112
-10.500 -1.0769 0.01736 0.01220 -0.0053 0.9572 0.0117
-10.250 -1.0528 0.01697 0.01176 -0.0047 0.9530 0.0122
-10.000 -1.0296 0.01657 0.01128 -0.0039 0.9488 0.0127
-9.750 -1.0055 0.01622 0.01086 -0.0032 0.9450 0.0130
-9.500 -0.9805 0.01574 0.01032 -0.0028 0.9416 0.0134
-9.250 -0.9562 0.01523 0.00975 -0.0022 0.9380 0.0140
-9.000 -0.9315 0.01487 0.00936 -0.0016 0.9347 0.0146
-8.750 -0.9063 0.01458 0.00902 -0.0011 0.9315 0.0151
-8.500 -0.8797 0.01424 0.00865 -0.0009 0.9286 0.0156
-8.250 -0.8535 0.01392 0.00829 -0.0006 0.9254 0.0162
-8.000 -0.8275 0.01362 0.00794 -0.0003 0.9223 0.0166
-7.750 -0.8016 0.01335 0.00760 0.0002 0.9194 0.0169
-7.500 -0.7759 0.01289 0.00711 0.0005 0.9165 0.0180
-7.250 -0.7487 0.01259 0.00681 0.0006 0.9136 0.0188
-7.000 -0.7216 0.01236 0.00657 0.0008 0.9105 0.0196
-6.750 -0.6946 0.01215 0.00633 0.0010 0.9076 0.0204
-6.500 -0.6676 0.01196 0.00610 0.0012 0.9049 0.0211
-6.250 -0.6409 0.01164 0.00574 0.0015 0.9021 0.0222
-6.000 -0.6132 0.01137 0.00550 0.0015 0.8992 0.0235
-5.750 -0.5854 0.01118 0.00531 0.0015 0.8961 0.0247
-5.500 -0.5579 0.01099 0.00510 0.0017 0.8930 0.0257
-5.250 -0.5308 0.01082 0.00490 0.0020 0.8895 0.0266
-5.000 -0.5034 0.01054 0.00460 0.0021 0.8853 0.0279
-4.750 -0.4759 0.01027 0.00434 0.0023 0.8805 0.0299
-4.500 -0.4486 0.01012 0.00418 0.0025 0.8758 0.0315
-4.250 -0.4209 0.00994 0.00398 0.0027 0.8712 0.0329
-4.000 -0.3924 0.00981 0.00385 0.0027 0.8660 0.0340
-3.750 -0.3653 0.00948 0.00349 0.0030 0.8607 0.0368
-3.500 -0.3374 0.00931 0.00333 0.0031 0.8550 0.0394
-3.250 -0.3088 0.00921 0.00324 0.0030 0.8488 0.0421
-3.000 -0.2807 0.00916 0.00318 0.0031 0.8431 0.0435
-2.750 -0.2526 0.00881 0.00282 0.0032 0.8364 0.0486
-2.500 -0.2244 0.00865 0.00265 0.0032 0.8295 0.0516
-2.250 -0.1957 0.00851 0.00250 0.0032 0.8215 0.0540
-2.000 -0.1674 0.00834 0.00229 0.0033 0.8134 0.0579
-1.750 -0.1387 0.00816 0.00214 0.0032 0.8055 0.0644
-1.500 -0.1101 0.00803 0.00200 0.0032 0.7977 0.0724
-1.250 -0.0815 0.00780 0.00187 0.0031 0.7884 0.0957
-1.000 -0.0553 0.00703 0.00167 0.0031 0.7783 0.2650
-0.750 -0.0295 0.00625 0.00151 0.0032 0.7647 0.4543
-0.500 -0.0031 0.00571 0.00142 0.0033 0.7468 0.5975
-0.250 0.0234 0.00536 0.00136 0.0037 0.7246 0.7028
0.000 0.0492 0.00509 0.00133 0.0043 0.6924 0.7972
0.250 0.0741 0.00501 0.00134 0.0052 0.6433 0.8766
0.500 0.0991 0.00518 0.00142 0.0062 0.5743 0.9369
0.750 0.1292 0.00561 0.00153 0.0058 0.4850 0.9630
1.000 0.1634 0.00617 0.00168 0.0042 0.3842 0.9786
1.250 0.2017 0.00660 0.00183 0.0018 0.3223 0.9859
1.500 0.2462 0.00692 0.00198 -0.0019 0.2896 0.9898
1.750 0.2842 0.00713 0.00208 -0.0042 0.2711 0.9930
2.000 0.3211 0.00730 0.00216 -0.0062 0.2583 0.9952
2.250 0.3591 0.00746 0.00224 -0.0085 0.2474 0.9967
2.500 0.3957 0.00758 0.00231 -0.0105 0.2400 0.9983
2.750 0.4315 0.00774 0.00241 -0.0123 0.2322 0.9997
3.000 0.4595 0.00779 0.00245 -0.0124 0.2283 1.0000
3.250 0.4854 0.00787 0.00249 -0.0121 0.2237 1.0000
3.500 0.5113 0.00799 0.00257 -0.0118 0.2182 1.0000
3.750 0.5371 0.00806 0.00264 -0.0114 0.2147 1.0000
4.000 0.5629 0.00814 0.00271 -0.0110 0.2110 1.0000
4.250 0.5887 0.00825 0.00280 -0.0106 0.2070 1.0000
4.500 0.6145 0.00843 0.00293 -0.0103 0.2016 1.0000
4.750 0.6404 0.00849 0.00301 -0.0099 0.1988 1.0000
5.000 0.6664 0.00858 0.00310 -0.0095 0.1948 1.0000
5.250 0.6922 0.00873 0.00322 -0.0092 0.1902 1.0000
5.500 0.7182 0.00888 0.00336 -0.0089 0.1857 1.0000
5.750 0.7443 0.00896 0.00345 -0.0085 0.1814 1.0000
6.000 0.7704 0.00910 0.00358 -0.0082 0.1769 1.0000
6.250 0.7964 0.00929 0.00374 -0.0080 0.1718 1.0000
6.500 0.8228 0.00938 0.00386 -0.0077 0.1674 1.0000
6.750 0.8489 0.00956 0.00400 -0.0075 0.1600 1.0000
7.000 0.8752 0.00971 0.00415 -0.0072 0.1553 1.0000
7.250 0.9014 0.00988 0.00431 -0.0070 0.1491 1.0000
7.500 0.9276 0.01008 0.00450 -0.0068 0.1424 1.0000
7.750 0.9537 0.01030 0.00469 -0.0066 0.1347 1.0000
8.000 0.9800 0.01053 0.00491 -0.0065 0.1273 1.0000
8.250 1.0058 0.01082 0.00517 -0.0063 0.1179 1.0000
8.500 1.0316 0.01113 0.00543 -0.0062 0.1073 1.0000
8.750 1.0569 0.01152 0.00576 -0.0060 0.0943 1.0000
9.000 1.0817 0.01199 0.00615 -0.0057 0.0801 1.0000
9.250 1.1061 0.01250 0.00660 -0.0055 0.0668 1.0000
9.500 1.1303 0.01303 0.00707 -0.0052 0.0555 1.0000
9.750 1.1542 0.01359 0.00757 -0.0049 0.0459 1.0000
10.000 1.1778 0.01416 0.00811 -0.0045 0.0380 1.0000
10.250 1.2012 0.01476 0.00867 -0.0041 0.0320 1.0000
10.500 1.2250 0.01524 0.00918 -0.0038 0.0285 1.0000
10.750 1.2475 0.01590 0.00982 -0.0033 0.0249 1.0000
11.000 1.2707 0.01642 0.01039 -0.0028 0.0230 1.0000
11.250 1.2936 0.01693 0.01094 -0.0024 0.0215 1.0000
11.500 1.3149 0.01761 0.01163 -0.0018 0.0197 1.0000
11.750 1.3351 0.01838 0.01246 -0.0010 0.0181 1.0000
12.000 1.3574 0.01884 0.01298 -0.0005 0.0174 1.0000
12.250 1.3786 0.01939 0.01357 0.0001 0.0165 1.0000
12.500 1.3983 0.02006 0.01427 0.0009 0.0156 1.0000
12.750 1.4156 0.02090 0.01515 0.0019 0.0147 1.0000
13.000 1.4287 0.02204 0.01640 0.0034 0.0138 1.0000
13.250 1.4464 0.02267 0.01710 0.0044 0.0136 1.0000
13.500 1.4620 0.02339 0.01789 0.0057 0.0133 1.0000
13.750 1.4728 0.02422 0.01880 0.0075 0.0129 1.0000
14.000 1.4827 0.02516 0.01981 0.0093 0.0126 1.0000
14.250 1.4922 0.02620 0.02093 0.0109 0.0123 1.0000
14.500 1.5006 0.02739 0.02219 0.0124 0.0119 1.0000
14.750 1.5077 0.02875 0.02363 0.0138 0.0116 1.0000
15.000 1.5123 0.03037 0.02534 0.0151 0.0113 1.0000
15.250 1.5134 0.03239 0.02745 0.0163 0.0110 1.0000
15.500 1.5098 0.03498 0.03016 0.0173 0.0108 1.0000
15.750 1.5003 0.03838 0.03371 0.0178 0.0105 1.0000
16.000 1.4894 0.04231 0.03779 0.0175 0.0103 1.0000
16.250 1.4856 0.04576 0.04136 0.0167 0.0103 1.0000
16.500 1.4784 0.05000 0.04573 0.0152 0.0102 1.0000
16.750 1.4647 0.05562 0.05150 0.0125 0.0102 1.0000
17.000 1.4419 0.06338 0.05945 0.0083 0.0102 1.0000
17.250 1.4091 0.07339 0.06966 0.0027 0.0102 1.0000
17.500 1.3688 0.08451 0.08097 -0.0029 0.0102 1.0000
17.750 1.3260 0.09555 0.09217 -0.0081 0.0103 1.0000
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Polar data table (+)
Polar graphs
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