NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il) Reynolds number: 50,000 Max Cl/Cd: 27.64 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ames03-il-50000-n5.txt Download as CSV file: xf-ames03-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4490 0.11855 0.11241 -0.0055 1.0000 0.0647
-10.750 -0.5950 0.12502 0.11869 0.0096 1.0000 0.0668
-10.500 -0.5859 0.12050 0.11416 0.0087 1.0000 0.0635
-10.000 -0.5968 0.10621 0.09994 -0.0040 1.0000 0.0549
-9.750 -0.5915 0.10160 0.09534 -0.0060 1.0000 0.0541
-9.500 -0.5892 0.09635 0.09011 -0.0094 1.0000 0.0533
-9.250 -0.5895 0.09038 0.08414 -0.0143 1.0000 0.0525
-9.000 -0.5938 0.08411 0.07786 -0.0199 1.0000 0.0516
-8.750 -0.6017 0.07857 0.07227 -0.0240 1.0000 0.0509
-8.500 -0.6078 0.07318 0.06674 -0.0272 1.0000 0.0503
-8.250 -0.6119 0.06802 0.06139 -0.0295 1.0000 0.0497
-8.000 -0.6133 0.06324 0.05635 -0.0309 1.0000 0.0495
-7.750 -0.6117 0.05895 0.05176 -0.0314 1.0000 0.0499
-7.500 -0.6082 0.05509 0.04754 -0.0312 1.0000 0.0508
-7.250 -0.6040 0.05160 0.04366 -0.0301 1.0000 0.0518
-7.000 -0.5992 0.04844 0.04009 -0.0284 1.0000 0.0527
-6.750 -0.5929 0.04551 0.03672 -0.0263 1.0000 0.0534
-6.500 -0.5835 0.04270 0.03343 -0.0242 1.0000 0.0538
-6.250 -0.5714 0.04006 0.03031 -0.0223 1.0000 0.0545
-6.000 -0.5567 0.03768 0.02745 -0.0205 1.0000 0.0555
-5.750 -0.5412 0.03572 0.02543 -0.0193 1.0000 0.0582
-5.500 -0.5237 0.03415 0.02367 -0.0180 1.0000 0.0615
-5.250 -0.5040 0.03242 0.02159 -0.0166 1.0000 0.0644
-5.000 -0.4825 0.03074 0.01953 -0.0153 1.0000 0.0670
-4.750 -0.4616 0.02931 0.01802 -0.0142 1.0000 0.0713
-4.500 -0.4403 0.02822 0.01682 -0.0131 1.0000 0.0775
-4.250 -0.4175 0.02709 0.01549 -0.0119 1.0000 0.0829
-4.000 -0.3901 0.02607 0.01445 -0.0120 0.9976 0.0932
-3.750 -0.3625 0.02507 0.01338 -0.0121 0.9955 0.1057
-3.500 -0.3349 0.02412 0.01243 -0.0124 0.9935 0.1270
-3.250 -0.3092 0.02299 0.01154 -0.0127 0.9911 0.1681
-3.000 -0.2865 0.02102 0.01073 -0.0130 0.9890 0.3371
-2.750 -0.2748 0.01976 0.01125 -0.0077 0.9873 0.7074
-2.500 -0.2519 0.02013 0.01171 -0.0040 0.9856 0.8490
-2.250 -0.1833 0.02085 0.01211 -0.0087 0.9885 0.9621
-2.000 -0.0956 0.02098 0.01176 -0.0204 0.9919 1.0000
-1.750 -0.0747 0.02091 0.01147 -0.0204 0.9875 1.0000
-1.500 -0.0515 0.02090 0.01126 -0.0208 0.9836 1.0000
-1.250 -0.0318 0.02093 0.01112 -0.0204 0.9792 1.0000
-1.000 -0.0087 0.02102 0.01105 -0.0206 0.9753 1.0000
-0.750 0.0142 0.02115 0.01104 -0.0206 0.9713 1.0000
-0.500 0.0381 0.02133 0.01108 -0.0208 0.9660 1.0000
-0.250 0.0741 0.02160 0.01123 -0.0231 0.9589 1.0000
0.000 0.1250 0.02191 0.01144 -0.0279 0.9478 1.0000
0.250 0.1743 0.02216 0.01164 -0.0321 0.9326 1.0000
0.500 0.2148 0.02239 0.01182 -0.0343 0.9163 1.0000
0.750 0.2523 0.02254 0.01195 -0.0356 0.8985 1.0000
1.000 0.2815 0.02258 0.01198 -0.0350 0.8785 1.0000
1.250 0.3045 0.02254 0.01193 -0.0333 0.8587 1.0000
1.500 0.3268 0.02250 0.01191 -0.0316 0.8424 1.0000
1.750 0.3482 0.02245 0.01189 -0.0298 0.8272 1.0000
2.000 0.3700 0.02230 0.01178 -0.0279 0.8104 1.0000
2.250 0.3920 0.02204 0.01158 -0.0257 0.7924 1.0000
2.500 0.4113 0.02181 0.01143 -0.0235 0.7691 1.0000
2.750 0.4315 0.02144 0.01114 -0.0212 0.7413 1.0000
3.000 0.4511 0.02111 0.01091 -0.0190 0.7019 1.0000
3.500 0.4946 0.01969 0.00897 -0.0117 0.5131 1.0000
3.750 0.5120 0.02023 0.00872 -0.0087 0.4348 1.0000
4.000 0.5319 0.02106 0.00916 -0.0075 0.3935 1.0000
4.250 0.5540 0.02182 0.00972 -0.0067 0.3668 1.0000
4.500 0.5769 0.02254 0.01027 -0.0060 0.3477 1.0000
4.750 0.6008 0.02323 0.01085 -0.0054 0.3320 1.0000
5.000 0.6254 0.02389 0.01146 -0.0049 0.3180 1.0000
5.250 0.6507 0.02455 0.01216 -0.0045 0.3055 1.0000
5.500 0.6765 0.02523 0.01286 -0.0041 0.2942 1.0000
5.750 0.7026 0.02595 0.01357 -0.0037 0.2836 1.0000
6.000 0.7289 0.02668 0.01437 -0.0035 0.2731 1.0000
6.250 0.7551 0.02747 0.01530 -0.0032 0.2627 1.0000
6.500 0.7810 0.02831 0.01618 -0.0030 0.2529 1.0000
6.750 0.8067 0.02919 0.01719 -0.0028 0.2428 1.0000
7.000 0.8319 0.03016 0.01837 -0.0026 0.2324 1.0000
7.250 0.8569 0.03114 0.01941 -0.0024 0.2232 1.0000
7.500 0.8810 0.03215 0.02063 -0.0022 0.2124 1.0000
7.750 0.9044 0.03330 0.02204 -0.0020 0.2019 1.0000
8.000 0.9275 0.03434 0.02325 -0.0017 0.1919 1.0000
8.250 0.9499 0.03539 0.02448 -0.0014 0.1814 1.0000
8.500 0.9704 0.03663 0.02605 -0.0010 0.1698 1.0000
8.750 0.9904 0.03786 0.02753 -0.0006 0.1590 1.0000
9.000 1.0097 0.03883 0.02866 0.0000 0.1484 1.0000
9.250 1.0283 0.03966 0.02963 0.0006 0.1380 1.0000
9.500 1.0435 0.04103 0.03132 0.0013 0.1265 1.0000
9.750 1.0573 0.04263 0.03319 0.0021 0.1160 1.0000
10.000 1.0702 0.04402 0.03474 0.0030 0.1068 1.0000
10.250 1.0828 0.04524 0.03600 0.0039 0.0988 1.0000
10.500 1.0883 0.04790 0.03905 0.0050 0.0910 1.0000
10.750 1.0989 0.04910 0.04016 0.0060 0.0852 1.0000
11.000 1.0944 0.05290 0.04451 0.0072 0.0803 1.0000
11.250 1.0924 0.05532 0.04707 0.0084 0.0762 1.0000
11.500 1.0943 0.05732 0.04902 0.0095 0.0728 1.0000
11.750 1.0762 0.06216 0.05428 0.0099 0.0711 1.0000
12.000 1.0542 0.06773 0.06017 0.0092 0.0702 1.0000
12.250 1.0265 0.07464 0.06735 0.0069 0.0700 1.0000
12.500 0.9916 0.08383 0.07674 0.0020 0.0706 1.0000
12.750 0.9508 0.09640 0.08940 -0.0061 0.0720 1.0000
13.000 0.9094 0.11147 0.10445 -0.0153 0.0728 1.0000
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Polar data table (+)
Polar graphs
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