NASA/AMES A-02 AIRFOIL (ames02-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/AMES A-02 AIRFOIL (ames02-il) Reynolds number: 100,000 Max Cl/Cd: 31.72 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ames02-il-100000.txt Download as CSV file: xf-ames02-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5610 0.08806 0.08352 0.0120 1.0000 0.1286
-7.750 -0.5881 0.08240 0.07793 0.0055 1.0000 0.1329
-7.500 -0.6270 0.07538 0.07082 -0.0038 1.0000 0.1340
-7.250 -0.5828 0.07335 0.06895 0.0054 1.0000 0.1407
-7.000 -0.6193 0.06595 0.06134 -0.0050 1.0000 0.1481
-6.750 -0.6728 0.07124 0.06642 0.0024 1.0000 0.1429
-6.500 -0.6674 0.06619 0.06124 -0.0010 1.0000 0.1526
-6.250 -0.6586 0.06200 0.05684 -0.0038 1.0000 0.1664
-6.000 -0.6401 0.05892 0.05383 -0.0027 1.0000 0.1749
-5.750 -0.6254 0.05525 0.05009 -0.0033 1.0000 0.1890
-5.500 -0.5924 0.03924 0.03191 -0.0106 1.0000 0.0859
-5.250 -0.5655 0.03340 0.02487 -0.0099 1.0000 0.0708
-5.000 -0.5391 0.03056 0.02153 -0.0096 1.0000 0.0710
-4.750 -0.5117 0.02784 0.01849 -0.0093 1.0000 0.0706
-4.500 -0.4833 0.02554 0.01582 -0.0089 1.0000 0.0708
-4.250 -0.4557 0.02357 0.01384 -0.0088 1.0000 0.0737
-4.000 -0.4272 0.02211 0.01215 -0.0084 1.0000 0.0783
-3.750 -0.3994 0.02043 0.01048 -0.0081 1.0000 0.0822
-3.500 -0.3718 0.01911 0.00920 -0.0078 1.0000 0.0899
-3.250 -0.3449 0.01785 0.00804 -0.0074 1.0000 0.1000
-3.000 -0.3187 0.01667 0.00706 -0.0070 1.0000 0.1169
-2.750 -0.2932 0.01534 0.00601 -0.0065 1.0000 0.1526
-2.500 -0.2809 0.01195 0.00530 -0.0036 1.0000 0.6328
-2.250 -0.2666 0.01155 0.00539 0.0014 1.0000 0.7979
-2.000 -0.2464 0.01144 0.00542 0.0053 1.0000 0.8853
-1.750 -0.1916 0.01166 0.00548 0.0022 1.0000 0.9629
-1.500 -0.1089 0.01184 0.00536 -0.0081 1.0000 1.0000
-1.250 -0.0885 0.01151 0.00493 -0.0079 1.0000 1.0000
-1.000 -0.0692 0.01125 0.00460 -0.0073 1.0000 1.0000
-0.750 -0.0512 0.01110 0.00437 -0.0063 1.0000 1.0000
-0.500 -0.0347 0.01104 0.00423 -0.0049 1.0000 1.0000
-0.250 -0.0184 0.01106 0.00418 -0.0033 1.0000 1.0000
0.000 -0.0006 0.01114 0.00420 -0.0020 1.0000 1.0000
0.250 0.0188 0.01126 0.00427 -0.0009 1.0000 1.0000
0.500 0.0394 0.01143 0.00440 -0.0001 1.0000 1.0000
0.750 0.0608 0.01163 0.00458 0.0005 1.0000 1.0000
1.000 0.0826 0.01186 0.00481 0.0010 1.0000 1.0000
1.250 0.1048 0.01214 0.00510 0.0013 1.0000 1.0000
1.500 0.1305 0.01244 0.00543 0.0009 0.9985 1.0000
1.750 0.2068 0.01243 0.00557 -0.0087 0.9763 1.0000
2.000 0.2755 0.01228 0.00559 -0.0161 0.9491 1.0000
2.250 0.3137 0.01224 0.00565 -0.0167 0.9125 1.0000
2.500 0.3354 0.01221 0.00567 -0.0136 0.8715 1.0000
2.750 0.3529 0.01214 0.00560 -0.0098 0.8230 1.0000
3.000 0.3699 0.01206 0.00543 -0.0057 0.7578 1.0000
3.250 0.3867 0.01219 0.00521 -0.0015 0.6396 1.0000
3.500 0.4042 0.01332 0.00520 0.0015 0.4285 1.0000
3.750 0.4274 0.01477 0.00577 0.0021 0.3003 1.0000
4.000 0.4528 0.01593 0.00648 0.0024 0.2394 1.0000
4.250 0.4788 0.01699 0.00724 0.0026 0.2015 1.0000
4.500 0.5052 0.01802 0.00813 0.0029 0.1743 1.0000
4.750 0.5317 0.01906 0.00901 0.0031 0.1541 1.0000
5.000 0.5582 0.02020 0.01001 0.0034 0.1383 1.0000
5.250 0.5850 0.02137 0.01115 0.0036 0.1254 1.0000
5.500 0.6121 0.02258 0.01243 0.0038 0.1146 1.0000
5.750 0.6391 0.02401 0.01398 0.0041 0.1059 1.0000
6.000 0.6658 0.02560 0.01568 0.0043 0.0988 1.0000
6.250 0.6921 0.02710 0.01719 0.0045 0.0926 1.0000
6.500 0.7183 0.02929 0.01988 0.0048 0.0878 1.0000
6.750 0.7437 0.03106 0.02163 0.0049 0.0837 1.0000
7.000 0.7672 0.03406 0.02530 0.0053 0.0804 1.0000
7.250 0.7887 0.03779 0.02966 0.0056 0.0794 1.0000
7.500 0.8068 0.04224 0.03471 0.0058 0.0791 1.0000
7.750 0.8205 0.04737 0.04044 0.0058 0.0793 1.0000
8.000 0.8310 0.05307 0.04657 0.0055 0.0815 1.0000
8.250 0.8496 0.05709 0.05052 0.0057 0.0831 1.0000
8.500 0.7783 0.08743 0.08240 -0.0129 0.1531 1.0000
8.750 0.7922 0.09233 0.08724 -0.0108 0.1508 1.0000
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Polar data table (+)
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