NACA 66-206 (naca66206-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-206 (naca66206-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.29 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66206-il-1000000.txt Download as CSV file: xf-naca66206-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-206
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5159 0.08473 0.08311 -0.0204 1.0000 0.0053
-8.000 -0.5171 0.08089 0.07929 -0.0227 1.0000 0.0054
-7.750 -0.5220 0.07699 0.07541 -0.0261 1.0000 0.0054
-7.500 -0.5195 0.07267 0.07108 -0.0294 1.0000 0.0054
-7.250 -0.5160 0.06835 0.06673 -0.0318 1.0000 0.0054
-7.000 -0.5112 0.06428 0.06261 -0.0333 1.0000 0.0054
-6.750 -0.5063 0.06026 0.05853 -0.0340 1.0000 0.0054
-6.500 -0.5034 0.05675 0.05496 -0.0333 1.0000 0.0054
-6.250 -0.4937 0.05260 0.05071 -0.0337 0.9991 0.0054
-6.000 -0.4670 0.04698 0.04492 -0.0377 0.9964 0.0054
-5.750 -0.4391 0.04157 0.03930 -0.0409 0.9939 0.0054
-5.500 -0.4129 0.03667 0.03416 -0.0429 0.9902 0.0054
-5.250 -0.3902 0.02801 0.02500 -0.0457 0.9861 0.0064
-5.000 -0.3554 0.03019 0.02727 -0.0468 0.9850 0.0107
-3.750 -0.2087 0.01285 0.00817 -0.0498 0.9677 0.0089
-3.500 -0.1832 0.01046 0.00552 -0.0487 0.9616 0.0084
-3.250 -0.1564 0.00932 0.00426 -0.0483 0.9566 0.0096
-3.000 -0.1287 0.00951 0.00443 -0.0483 0.9511 0.0110
-2.750 -0.1055 0.00802 0.00279 -0.0474 0.9448 0.0126
-2.500 -0.0796 0.00751 0.00223 -0.0471 0.9395 0.0154
-2.250 -0.0532 0.00722 0.00187 -0.0467 0.9336 0.0187
-2.000 -0.0265 0.00703 0.00161 -0.0465 0.9287 0.0203
-1.750 0.0001 0.00673 0.00124 -0.0463 0.9230 0.0257
-1.500 0.0263 0.00628 0.00102 -0.0461 0.9178 0.1093
-1.250 0.0483 0.00474 0.00082 -0.0461 0.9124 0.5475
-1.000 0.0719 0.00411 0.00084 -0.0454 0.9068 0.7515
-0.750 0.0972 0.00400 0.00086 -0.0447 0.9020 0.8128
-0.500 0.1222 0.00395 0.00091 -0.0439 0.8957 0.8517
-0.250 0.1474 0.00395 0.00094 -0.0432 0.8890 0.8734
0.000 0.1724 0.00395 0.00094 -0.0424 0.8782 0.8890
0.250 0.1970 0.00396 0.00093 -0.0414 0.8646 0.9007
0.500 0.2226 0.00396 0.00094 -0.0408 0.8532 0.9085
0.750 0.2491 0.00398 0.00094 -0.0405 0.8418 0.9154
1.000 0.2747 0.00399 0.00093 -0.0399 0.8262 0.9208
1.250 0.2997 0.00406 0.00092 -0.0392 0.7967 0.9269
1.500 0.3227 0.00423 0.00089 -0.0380 0.7342 0.9329
1.750 0.3383 0.00523 0.00102 -0.0357 0.5017 0.9413
2.000 0.3551 0.00629 0.00131 -0.0339 0.2753 0.9499
2.250 0.3730 0.00737 0.00161 -0.0324 0.0541 0.9596
2.500 0.3973 0.00771 0.00189 -0.0317 0.0252 0.9692
2.750 0.4263 0.00791 0.00210 -0.0321 0.0188 0.9778
3.000 0.4560 0.00881 0.00318 -0.0326 0.0145 0.9868
3.250 0.4882 0.00928 0.00369 -0.0338 0.0139 0.9973
3.500 0.5147 0.00977 0.00426 -0.0337 0.0135 1.0000
3.750 0.5409 0.01018 0.00470 -0.0335 0.0122 1.0000
4.000 0.5667 0.01071 0.00527 -0.0333 0.0101 1.0000
4.250 0.5932 0.01105 0.00561 -0.0332 0.0086 1.0000
4.500 0.6161 0.01263 0.00730 -0.0323 0.0076 1.0000
4.750 0.6407 0.01433 0.00919 -0.0316 0.0065 1.0000
5.000 0.6668 0.01561 0.01062 -0.0311 0.0054 1.0000
5.250 0.6896 0.02002 0.01553 -0.0291 0.0055 1.0000
6.500 0.7299 0.03418 0.03182 -0.0180 0.0069 1.0000
6.750 0.7381 0.03900 0.03684 -0.0168 0.0069 1.0000
7.000 0.7439 0.04400 0.04201 -0.0157 0.0069 1.0000
7.250 0.7466 0.04913 0.04730 -0.0148 0.0069 1.0000
7.500 0.7464 0.05422 0.05251 -0.0141 0.0069 1.0000
7.750 0.7425 0.05916 0.05757 -0.0136 0.0069 1.0000
8.000 0.7327 0.06381 0.06231 -0.0129 0.0069 1.0000
8.250 0.7154 0.06775 0.06632 -0.0121 0.0069 1.0000
8.500 0.6979 0.07282 0.07144 -0.0140 0.0069 1.0000
8.750 0.6823 0.07967 0.07832 -0.0194 0.0069 1.0000
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Polar data table (+)
Polar graphs
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