NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-64 (naca001064-il) Reynolds number: 500,000 Max Cl/Cd: 53.66 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001064-il-500000-n5.txt Download as CSV file: xf-naca001064-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-64
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -1.1037 0.08161 0.07874 -0.0186 1.0000 0.0080
-15.750 -1.1511 0.06627 0.06307 -0.0291 1.0000 0.0078
-15.500 -1.1767 0.05756 0.05414 -0.0350 1.0000 0.0077
-15.250 -1.1965 0.05116 0.04753 -0.0384 1.0000 0.0078
-15.000 -1.2119 0.04626 0.04244 -0.0400 1.0000 0.0078
-14.750 -1.2233 0.04239 0.03839 -0.0403 1.0000 0.0079
-14.500 -1.2305 0.03933 0.03517 -0.0398 1.0000 0.0081
-14.250 -1.2340 0.03685 0.03255 -0.0386 1.0000 0.0082
-14.000 -1.2344 0.03480 0.03035 -0.0371 1.0000 0.0084
-13.750 -1.2322 0.03306 0.02848 -0.0353 1.0000 0.0086
-13.500 -1.2281 0.03153 0.02680 -0.0333 1.0000 0.0088
-13.250 -1.2224 0.03016 0.02530 -0.0312 1.0000 0.0091
-13.000 -1.2155 0.02891 0.02391 -0.0290 1.0000 0.0094
-12.750 -1.2077 0.02775 0.02261 -0.0267 1.0000 0.0097
-12.500 -1.1982 0.02668 0.02139 -0.0244 1.0000 0.0100
-12.250 -1.1857 0.02567 0.02021 -0.0225 1.0000 0.0103
-12.000 -1.1727 0.02461 0.01904 -0.0208 1.0000 0.0108
-11.750 -1.1573 0.02376 0.01812 -0.0193 1.0000 0.0114
-11.500 -1.1400 0.02306 0.01735 -0.0180 1.0000 0.0121
-11.250 -1.1223 0.02238 0.01658 -0.0166 1.0000 0.0127
-11.000 -1.1048 0.02166 0.01576 -0.0152 1.0000 0.0134
-10.750 -1.0871 0.02096 0.01494 -0.0138 1.0000 0.0140
-10.500 -1.0694 0.02031 0.01422 -0.0124 1.0000 0.0148
-10.250 -1.0498 0.01989 0.01378 -0.0111 1.0000 0.0157
-10.000 -1.0300 0.01953 0.01337 -0.0099 1.0000 0.0167
-9.750 -1.0108 0.01912 0.01290 -0.0085 1.0000 0.0178
-9.500 -0.9918 0.01870 0.01239 -0.0071 1.0000 0.0187
-9.000 -0.9553 0.01780 0.01140 -0.0039 1.0000 0.0205
-8.750 -0.9360 0.01750 0.01107 -0.0025 1.0000 0.0215
-8.500 -0.9169 0.01719 0.01072 -0.0009 1.0000 0.0227
-8.250 -0.8979 0.01687 0.01033 0.0006 1.0000 0.0238
-8.000 -0.8789 0.01656 0.00996 0.0022 1.0000 0.0246
-7.750 -0.8589 0.01630 0.00962 0.0036 0.9999 0.0252
-7.500 -0.8313 0.01550 0.00877 0.0031 0.9982 0.0267
-7.250 -0.8018 0.01503 0.00828 0.0023 0.9964 0.0280
-7.000 -0.7712 0.01464 0.00786 0.0013 0.9948 0.0292
-6.750 -0.7416 0.01426 0.00743 0.0006 0.9929 0.0305
-6.500 -0.7123 0.01387 0.00699 0.0000 0.9906 0.0315
-6.250 -0.6819 0.01352 0.00659 -0.0008 0.9884 0.0325
-6.000 -0.6508 0.01318 0.00620 -0.0018 0.9866 0.0330
-5.750 -0.6201 0.01264 0.00562 -0.0027 0.9850 0.0344
-5.500 -0.5916 0.01224 0.00520 -0.0031 0.9820 0.0361
-5.250 -0.5616 0.01191 0.00486 -0.0038 0.9793 0.0375
-5.000 -0.5302 0.01160 0.00453 -0.0048 0.9771 0.0388
-4.750 -0.4983 0.01132 0.00422 -0.0059 0.9752 0.0404
-4.500 -0.4674 0.01107 0.00394 -0.0067 0.9727 0.0420
-4.250 -0.4397 0.01080 0.00369 -0.0067 0.9683 0.0456
-4.000 -0.4097 0.01053 0.00345 -0.0074 0.9649 0.0522
-3.750 -0.3791 0.01022 0.00322 -0.0081 0.9622 0.0679
-3.500 -0.3525 0.00994 0.00303 -0.0080 0.9571 0.0875
-3.250 -0.3247 0.00965 0.00283 -0.0081 0.9523 0.1099
-3.000 -0.2958 0.00932 0.00264 -0.0085 0.9485 0.1431
-2.750 -0.2701 0.00901 0.00249 -0.0082 0.9424 0.1817
-2.500 -0.2438 0.00867 0.00232 -0.0080 0.9366 0.2268
-2.250 -0.2188 0.00813 0.00212 -0.0077 0.9313 0.3155
-2.000 -0.1964 0.00760 0.00196 -0.0068 0.9236 0.4095
-1.750 -0.1726 0.00708 0.00179 -0.0061 0.9176 0.5067
-1.500 -0.1506 0.00666 0.00171 -0.0050 0.9093 0.5919
-1.250 -0.1266 0.00633 0.00164 -0.0040 0.9026 0.6642
-1.000 -0.1037 0.00607 0.00164 -0.0028 0.8940 0.7306
-0.750 -0.0781 0.00593 0.00164 -0.0020 0.8866 0.7737
-0.500 -0.0524 0.00585 0.00166 -0.0013 0.8776 0.8054
-0.250 -0.0263 0.00580 0.00170 -0.0007 0.8684 0.8342
0.000 0.0000 0.00579 0.00171 0.0000 0.8548 0.8549
0.250 0.0263 0.00580 0.00170 0.0007 0.8341 0.8684
0.500 0.0524 0.00585 0.00166 0.0014 0.8053 0.8776
0.750 0.0781 0.00593 0.00164 0.0020 0.7738 0.8866
1.000 0.1037 0.00607 0.00164 0.0028 0.7315 0.8940
1.250 0.1267 0.00633 0.00164 0.0040 0.6648 0.9026
1.500 0.1507 0.00665 0.00171 0.0049 0.5937 0.9093
1.750 0.1726 0.00708 0.00179 0.0061 0.5065 0.9177
2.000 0.1963 0.00761 0.00196 0.0069 0.4086 0.9236
2.250 0.2188 0.00813 0.00212 0.0077 0.3148 0.9313
2.500 0.2438 0.00868 0.00232 0.0080 0.2265 0.9366
2.750 0.2701 0.00902 0.00249 0.0082 0.1815 0.9424
3.000 0.2958 0.00932 0.00264 0.0085 0.1434 0.9485
3.250 0.3247 0.00965 0.00283 0.0081 0.1099 0.9523
3.500 0.3525 0.00994 0.00303 0.0080 0.0875 0.9571
3.750 0.3791 0.01022 0.00322 0.0081 0.0679 0.9622
4.000 0.4097 0.01053 0.00345 0.0073 0.0522 0.9649
4.250 0.4397 0.01080 0.00369 0.0067 0.0455 0.9683
4.500 0.4674 0.01107 0.00394 0.0067 0.0420 0.9727
4.750 0.4983 0.01132 0.00422 0.0058 0.0404 0.9752
5.000 0.5303 0.01160 0.00453 0.0048 0.0388 0.9771
5.250 0.5617 0.01191 0.00486 0.0038 0.0375 0.9793
5.500 0.5917 0.01224 0.00520 0.0031 0.0361 0.9820
5.750 0.6202 0.01264 0.00563 0.0027 0.0344 0.9850
6.000 0.6509 0.01318 0.00620 0.0018 0.0330 0.9866
6.250 0.6820 0.01352 0.00659 0.0008 0.0325 0.9885
6.500 0.7123 0.01387 0.00699 0.0000 0.0315 0.9906
6.750 0.7417 0.01426 0.00743 -0.0006 0.0305 0.9930
7.000 0.7714 0.01464 0.00786 -0.0014 0.0292 0.9948
7.250 0.8019 0.01503 0.00828 -0.0023 0.0280 0.9964
7.500 0.8315 0.01550 0.00877 -0.0031 0.0267 0.9982
7.750 0.8590 0.01630 0.00963 -0.0036 0.0252 0.9999
8.000 0.8789 0.01656 0.00996 -0.0022 0.0246 1.0000
8.250 0.8979 0.01687 0.01033 -0.0006 0.0238 1.0000
8.500 0.9168 0.01719 0.01072 0.0009 0.0227 1.0000
8.750 0.9360 0.01750 0.01107 0.0025 0.0215 1.0000
9.000 0.9552 0.01780 0.01140 0.0039 0.0205 1.0000
9.250 0.9740 0.01817 0.01181 0.0054 0.0196 1.0000
9.500 0.9918 0.01870 0.01239 0.0071 0.0187 1.0000
9.750 1.0109 0.01912 0.01289 0.0085 0.0178 1.0000
10.000 1.0300 0.01953 0.01338 0.0099 0.0167 1.0000
10.250 1.0498 0.01989 0.01378 0.0111 0.0157 1.0000
10.500 1.0694 0.02031 0.01421 0.0123 0.0148 1.0000
10.750 1.0872 0.02096 0.01494 0.0138 0.0140 1.0000
11.000 1.1049 0.02166 0.01576 0.0152 0.0134 1.0000
11.250 1.1225 0.02238 0.01658 0.0166 0.0127 1.0000
11.500 1.1402 0.02306 0.01735 0.0179 0.0121 1.0000
11.750 1.1574 0.02376 0.01812 0.0192 0.0114 1.0000
12.000 1.1730 0.02461 0.01904 0.0207 0.0108 1.0000
12.250 1.1859 0.02567 0.02022 0.0225 0.0103 1.0000
12.500 1.1985 0.02668 0.02140 0.0243 0.0100 1.0000
12.750 1.2081 0.02776 0.02261 0.0266 0.0097 1.0000
13.000 1.2160 0.02891 0.02391 0.0289 0.0094 1.0000
13.250 1.2229 0.03017 0.02530 0.0311 0.0091 1.0000
13.500 1.2285 0.03154 0.02681 0.0332 0.0088 1.0000
13.750 1.2328 0.03306 0.02847 0.0352 0.0086 1.0000
14.000 1.2350 0.03481 0.03036 0.0370 0.0084 1.0000
14.250 1.2347 0.03686 0.03255 0.0385 0.0082 1.0000
14.500 1.2314 0.03932 0.03517 0.0396 0.0081 1.0000
14.750 1.2242 0.04239 0.03839 0.0402 0.0079 1.0000
15.000 1.2131 0.04623 0.04241 0.0399 0.0078 1.0000
15.250 1.1977 0.05114 0.04751 0.0382 0.0078 1.0000
15.500 1.1783 0.05750 0.05407 0.0348 0.0077 1.0000
15.750 1.1526 0.06625 0.06306 0.0289 0.0078 1.0000
16.000 1.1041 0.08188 0.07902 0.0181 0.0080 1.0000
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