NACA 63-206 (naca63206-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-206 (naca63206-il) Reynolds number: 1,000,000 Max Cl/Cd: 69.01 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca63206-il-1000000-n5.txt Download as CSV file: xf-naca63206-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-206
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5708 0.09012 0.08852 -0.0019 1.0000 0.0019
-8.500 -0.5675 0.08645 0.08487 -0.0039 1.0000 0.0019
-8.250 -0.5657 0.08274 0.08118 -0.0060 1.0000 0.0019
-8.000 -0.5660 0.07882 0.07729 -0.0083 1.0000 0.0019
-7.750 -0.5712 0.07428 0.07277 -0.0120 1.0000 0.0018
-7.500 -0.5687 0.06780 0.06628 -0.0200 1.0000 0.0017
-7.250 -0.5624 0.06181 0.06022 -0.0256 1.0000 0.0017
-7.000 -0.5540 0.05561 0.05392 -0.0301 1.0000 0.0017
-6.750 -0.5427 0.04954 0.04770 -0.0333 1.0000 0.0016
-6.500 -0.5289 0.04325 0.04120 -0.0356 1.0000 0.0016
-6.250 -0.5129 0.03646 0.03410 -0.0370 1.0000 0.0016
-6.000 -0.4949 0.02886 0.02606 -0.0374 1.0000 0.0017
-5.750 -0.4790 0.01379 0.00950 -0.0361 1.0000 0.0022
-5.500 -0.4541 0.01301 0.00859 -0.0357 1.0000 0.0024
-5.250 -0.4272 0.01222 0.00768 -0.0358 0.9991 0.0026
-4.750 -0.3642 0.01042 0.00555 -0.0379 0.9904 0.0032
-4.500 -0.3320 0.00991 0.00497 -0.0390 0.9849 0.0037
-4.250 -0.2998 0.00928 0.00425 -0.0402 0.9784 0.0041
-4.000 -0.2679 0.00819 0.00298 -0.0412 0.9698 0.0053
-3.750 -0.2362 0.00797 0.00276 -0.0421 0.9594 0.0069
-3.500 -0.2062 0.00775 0.00249 -0.0427 0.9465 0.0086
-3.250 -0.1781 0.00782 0.00256 -0.0427 0.9321 0.0094
-3.000 -0.1511 0.00730 0.00185 -0.0425 0.9172 0.0112
-2.750 -0.1242 0.00706 0.00149 -0.0423 0.9028 0.0126
-2.500 -0.0972 0.00689 0.00126 -0.0421 0.8886 0.0152
-2.250 -0.0701 0.00678 0.00108 -0.0419 0.8740 0.0189
-2.000 -0.0430 0.00667 0.00094 -0.0417 0.8593 0.0273
-1.750 -0.0157 0.00655 0.00080 -0.0416 0.8448 0.0451
-1.500 0.0115 0.00630 0.00068 -0.0416 0.8305 0.1068
-1.250 0.0384 0.00566 0.00055 -0.0419 0.8168 0.2856
-1.000 0.0653 0.00506 0.00046 -0.0422 0.8039 0.4657
-0.750 0.0922 0.00468 0.00045 -0.0422 0.7909 0.5964
-0.500 0.1192 0.00448 0.00046 -0.0421 0.7781 0.6791
-0.250 0.1464 0.00441 0.00047 -0.0420 0.7648 0.7207
0.000 0.1737 0.00440 0.00047 -0.0418 0.7486 0.7451
0.250 0.2009 0.00442 0.00049 -0.0417 0.7287 0.7666
0.500 0.2281 0.00446 0.00051 -0.0415 0.7084 0.7824
0.750 0.2551 0.00453 0.00054 -0.0413 0.6840 0.7971
1.000 0.2819 0.00464 0.00058 -0.0411 0.6478 0.8118
1.250 0.3072 0.00497 0.00063 -0.0407 0.5637 0.8269
1.500 0.3302 0.00584 0.00080 -0.0401 0.3655 0.8427
1.750 0.3540 0.00666 0.00106 -0.0398 0.1948 0.8591
2.000 0.3792 0.00708 0.00125 -0.0395 0.1143 0.8762
2.250 0.4043 0.00740 0.00143 -0.0390 0.0575 0.8949
2.750 0.4541 0.00775 0.00175 -0.0377 0.0212 0.9361
3.000 0.4798 0.00792 0.00197 -0.0372 0.0155 0.9627
3.250 0.5103 0.00818 0.00233 -0.0378 0.0138 1.0000
3.500 0.5371 0.00861 0.00286 -0.0376 0.0127 1.0000
3.750 0.5646 0.00877 0.00302 -0.0377 0.0124 1.0000
4.000 0.5922 0.00887 0.00310 -0.0378 0.0113 1.0000
4.250 0.6194 0.00911 0.00339 -0.0377 0.0094 1.0000
4.500 0.6464 0.00940 0.00369 -0.0377 0.0076 1.0000
4.750 0.6725 0.00991 0.00424 -0.0375 0.0055 1.0000
5.000 0.6994 0.01017 0.00453 -0.0374 0.0049 1.0000
5.250 0.7258 0.01053 0.00492 -0.0373 0.0040 1.0000
5.500 0.7522 0.01090 0.00529 -0.0372 0.0031 1.0000
5.750 0.7760 0.01211 0.00668 -0.0365 0.0024 1.0000
6.000 0.8008 0.01303 0.00775 -0.0360 0.0022 1.0000
6.250 0.8245 0.01438 0.00931 -0.0353 0.0021 1.0000
6.500 0.8475 0.01628 0.01154 -0.0345 0.0020 1.0000
6.750 0.8683 0.01954 0.01528 -0.0332 0.0020 1.0000
7.000 0.8746 0.03074 0.02756 -0.0294 0.0021 1.0000
7.250 0.8841 0.03834 0.03566 -0.0274 0.0020 1.0000
7.500 0.8935 0.04454 0.04220 -0.0261 0.0019 1.0000
7.750 0.8999 0.05069 0.04863 -0.0253 0.0018 1.0000
8.000 0.9022 0.05688 0.05505 -0.0250 0.0018 1.0000
8.250 0.9009 0.06289 0.06125 -0.0254 0.0017 1.0000
8.500 0.8945 0.06888 0.06738 -0.0264 0.0017 1.0000
8.750 0.8829 0.07455 0.07316 -0.0280 0.0017 1.0000
9.000 0.8642 0.07965 0.07831 -0.0305 0.0018 1.0000
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Polar data table (+)
Polar graphs
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