NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(2)-415 (naca652415-il) Reynolds number: 200,000 Max Cl/Cd: 67.97 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca652415-il-200000-n5.txt Download as CSV file: xf-naca652415-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5620 0.07687 0.07286 -0.0733 1.0000 0.0213
-12.750 -0.5914 0.06887 0.06474 -0.0784 1.0000 0.0211
-12.500 -0.6228 0.06217 0.05787 -0.0816 1.0000 0.0211
-12.250 -0.6488 0.05718 0.05271 -0.0829 1.0000 0.0211
-12.000 -0.6739 0.05312 0.04849 -0.0826 1.0000 0.0211
-11.750 -0.6989 0.04996 0.04517 -0.0807 1.0000 0.0212
-11.500 -0.7180 0.04575 0.04059 -0.0811 0.9879 0.0214
-11.250 -0.7099 0.04275 0.03739 -0.0835 0.9767 0.0218
-11.000 -0.6949 0.04075 0.03526 -0.0853 0.9662 0.0223
-10.750 -0.6776 0.03911 0.03349 -0.0867 0.9563 0.0229
-10.500 -0.6607 0.03696 0.03108 -0.0879 0.9474 0.0235
-10.250 -0.6471 0.03468 0.02848 -0.0880 0.9368 0.0241
-10.000 -0.6311 0.03240 0.02583 -0.0881 0.9278 0.0248
-9.750 -0.6140 0.03041 0.02349 -0.0877 0.9186 0.0254
-9.500 -0.5964 0.02889 0.02158 -0.0870 0.9096 0.0261
-9.250 -0.5751 0.02744 0.02002 -0.0869 0.9020 0.0269
-9.000 -0.5540 0.02646 0.01895 -0.0866 0.8944 0.0277
-8.750 -0.5324 0.02544 0.01780 -0.0861 0.8867 0.0284
-8.500 -0.5099 0.02441 0.01661 -0.0856 0.8799 0.0291
-8.250 -0.4878 0.02347 0.01554 -0.0851 0.8723 0.0299
-8.000 -0.4644 0.02264 0.01454 -0.0846 0.8664 0.0309
-7.750 -0.4424 0.02194 0.01370 -0.0839 0.8590 0.0319
-7.500 -0.4198 0.02097 0.01268 -0.0834 0.8529 0.0328
-7.250 -0.3984 0.02020 0.01189 -0.0827 0.8464 0.0336
-7.000 -0.3773 0.01954 0.01120 -0.0819 0.8396 0.0345
-6.500 -0.3346 0.01838 0.00992 -0.0803 0.8275 0.0368
-6.250 -0.3128 0.01789 0.00933 -0.0796 0.8218 0.0384
-6.000 -0.2916 0.01731 0.00869 -0.0788 0.8166 0.0399
-5.750 -0.2711 0.01676 0.00814 -0.0780 0.8100 0.0417
-5.500 -0.2487 0.01630 0.00761 -0.0774 0.8047 0.0438
-5.250 -0.2254 0.01590 0.00712 -0.0770 0.7999 0.0463
-5.000 -0.2026 0.01548 0.00668 -0.0764 0.7942 0.0499
-4.750 -0.1787 0.01511 0.00627 -0.0761 0.7893 0.0560
-4.500 -0.1544 0.01469 0.00583 -0.0758 0.7850 0.0670
-4.250 -0.1316 0.01420 0.00547 -0.0754 0.7793 0.0941
-4.000 -0.1113 0.01329 0.00502 -0.0749 0.7743 0.1943
-3.750 -0.0932 0.01197 0.00448 -0.0745 0.7703 0.3850
-3.500 -0.0712 0.01148 0.00457 -0.0738 0.7656 0.5301
-3.250 -0.0447 0.01147 0.00461 -0.0735 0.7608 0.5738
-3.000 -0.0181 0.01156 0.00474 -0.0731 0.7567 0.6183
-2.750 0.0077 0.01186 0.00510 -0.0722 0.7531 0.6567
-2.500 0.0339 0.01203 0.00528 -0.0716 0.7484 0.6729
-2.250 0.0620 0.01204 0.00520 -0.0718 0.7443 0.6793
-2.000 0.0905 0.01201 0.00507 -0.0721 0.7406 0.6837
-1.750 0.1191 0.01200 0.00499 -0.0722 0.7374 0.6870
-1.500 0.1464 0.01201 0.00497 -0.0723 0.7327 0.6909
-1.250 0.1746 0.01200 0.00491 -0.0725 0.7286 0.6951
-1.000 0.2034 0.01199 0.00482 -0.0729 0.7252 0.6995
-0.750 0.2318 0.01200 0.00479 -0.0731 0.7223 0.7025
-0.500 0.2594 0.01203 0.00482 -0.0732 0.7183 0.7060
-0.250 0.2871 0.01205 0.00483 -0.0734 0.7141 0.7100
0.000 0.3157 0.01207 0.00481 -0.0737 0.7104 0.7146
0.250 0.3441 0.01210 0.00482 -0.0739 0.7075 0.7180
0.500 0.3723 0.01214 0.00486 -0.0741 0.7045 0.7213
0.750 0.3994 0.01220 0.00495 -0.0741 0.7003 0.7253
1.000 0.4274 0.01225 0.00501 -0.0744 0.6965 0.7300
1.250 0.4556 0.01229 0.00506 -0.0746 0.6933 0.7340
1.500 0.4840 0.01234 0.00513 -0.0748 0.6905 0.7374
1.750 0.5112 0.01242 0.00526 -0.0749 0.6869 0.7415
2.000 0.5385 0.01251 0.00539 -0.0750 0.6828 0.7463
2.250 0.5662 0.01258 0.00551 -0.0751 0.6793 0.7507
2.500 0.5939 0.01265 0.00563 -0.0752 0.6761 0.7546
2.750 0.6224 0.01273 0.00574 -0.0754 0.6732 0.7591
3.000 0.6488 0.01285 0.00595 -0.0754 0.6689 0.7642
3.250 0.6753 0.01294 0.00613 -0.0753 0.6647 0.7685
3.500 0.7027 0.01300 0.00627 -0.0753 0.6605 0.7732
3.750 0.7299 0.01307 0.00639 -0.0753 0.6553 0.7787
4.000 0.7556 0.01314 0.00656 -0.0750 0.6486 0.7837
4.250 0.7831 0.01314 0.00661 -0.0748 0.6425 0.7882
4.500 0.8068 0.01317 0.00675 -0.0741 0.6318 0.7938
4.750 0.8309 0.01308 0.00669 -0.0732 0.6154 0.7998
5.000 0.8516 0.01298 0.00659 -0.0716 0.5897 0.8053
5.250 0.8716 0.01300 0.00658 -0.0700 0.5575 0.8120
5.500 0.8918 0.01312 0.00669 -0.0685 0.5274 0.8179
5.750 0.9084 0.01338 0.00682 -0.0664 0.4819 0.8244
6.000 0.9140 0.01410 0.00714 -0.0625 0.4015 0.8324
6.250 0.9108 0.01518 0.00782 -0.0574 0.3240 0.8411
6.500 0.9052 0.01628 0.00859 -0.0520 0.2563 0.8510
6.750 0.9008 0.01744 0.00945 -0.0471 0.1968 0.8624
7.000 0.8989 0.01858 0.01036 -0.0429 0.1462 0.8738
7.250 0.8992 0.01973 0.01131 -0.0391 0.1037 0.8869
7.500 0.9024 0.02078 0.01224 -0.0359 0.0755 0.9024
7.750 0.9084 0.02171 0.01313 -0.0332 0.0592 0.9221
8.000 0.9185 0.02259 0.01402 -0.0313 0.0496 0.9500
8.250 0.9330 0.02350 0.01496 -0.0305 0.0435 1.0000
8.500 0.9456 0.02463 0.01607 -0.0296 0.0391 1.0000
8.750 0.9597 0.02567 0.01718 -0.0287 0.0364 1.0000
9.000 0.9724 0.02680 0.01835 -0.0277 0.0342 1.0000
9.250 0.9818 0.02819 0.01973 -0.0265 0.0323 1.0000
9.500 0.9947 0.02935 0.02097 -0.0256 0.0306 1.0000
9.750 1.0071 0.03055 0.02223 -0.0247 0.0292 1.0000
10.000 1.0184 0.03186 0.02359 -0.0238 0.0280 1.0000
10.250 1.0281 0.03332 0.02508 -0.0228 0.0270 1.0000
10.500 1.0362 0.03495 0.02673 -0.0217 0.0261 1.0000
10.750 1.0481 0.03632 0.02818 -0.0209 0.0254 1.0000
11.000 1.0599 0.03773 0.02967 -0.0201 0.0248 1.0000
11.250 1.0718 0.03917 0.03119 -0.0193 0.0241 1.0000
11.500 1.0841 0.04060 0.03269 -0.0186 0.0235 1.0000
11.750 1.0963 0.04206 0.03420 -0.0179 0.0228 1.0000
12.000 1.1087 0.04354 0.03573 -0.0173 0.0223 1.0000
12.250 1.1204 0.04509 0.03729 -0.0168 0.0216 1.0000
12.500 1.1338 0.04668 0.03892 -0.0162 0.0211 1.0000
12.750 1.1463 0.04827 0.04069 -0.0156 0.0206 1.0000
13.000 1.1591 0.04995 0.04250 -0.0151 0.0202 1.0000
13.250 1.1710 0.05175 0.04445 -0.0146 0.0198 1.0000
13.500 1.1819 0.05368 0.04653 -0.0141 0.0194 1.0000
13.750 1.1913 0.05578 0.04878 -0.0136 0.0191 1.0000
14.000 1.1989 0.05805 0.05123 -0.0132 0.0188 1.0000
14.250 1.2049 0.06049 0.05384 -0.0129 0.0186 1.0000
14.500 1.2090 0.06314 0.05665 -0.0127 0.0183 1.0000
14.750 1.2114 0.06600 0.05968 -0.0126 0.0181 1.0000
15.000 1.2121 0.06910 0.06295 -0.0127 0.0180 1.0000
15.250 1.2112 0.07240 0.06642 -0.0130 0.0178 1.0000
15.500 1.2093 0.07587 0.07004 -0.0134 0.0176 1.0000
15.750 1.2062 0.07958 0.07390 -0.0141 0.0175 1.0000
16.000 1.2020 0.08356 0.07803 -0.0150 0.0173 1.0000
16.250 1.1953 0.08801 0.08264 -0.0162 0.0172 1.0000
16.500 1.1814 0.09362 0.08849 -0.0181 0.0170 1.0000
16.750 1.1655 0.09987 0.09499 -0.0207 0.0170 1.0000
17.000 1.1483 0.10668 0.10205 -0.0239 0.0170 1.0000
17.250 1.1277 0.11449 0.11012 -0.0281 0.0169 1.0000
17.500 1.1063 0.12306 0.11892 -0.0332 0.0169 1.0000
17.750 1.0836 0.13253 0.12861 -0.0391 0.0169 1.0000
18.000 1.0584 0.14342 0.13970 -0.0463 0.0170 1.0000
18.250 1.0289 0.15650 0.15297 -0.0551 0.0171 1.0000
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