NACA 0010 (naca0010-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010 (naca0010-il) Reynolds number: 200,000 Max Cl/Cd: 42.23 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0010-il-200000-n5.txt Download as CSV file: xf-naca0010-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.9542 0.08870 0.08477 -0.0028 1.0000 0.0176
-13.750 -0.9842 0.07796 0.07388 -0.0102 1.0000 0.0173
-13.500 -1.0102 0.06862 0.06433 -0.0171 1.0000 0.0172
-13.250 -1.0325 0.06085 0.05632 -0.0227 1.0000 0.0172
-13.000 -1.0511 0.05461 0.04982 -0.0265 1.0000 0.0173
-12.750 -1.0665 0.04964 0.04455 -0.0285 1.0000 0.0175
-12.500 -1.0782 0.04575 0.04039 -0.0289 1.0000 0.0178
-12.250 -1.0825 0.04313 0.03764 -0.0282 1.0000 0.0181
-12.000 -1.0817 0.04130 0.03571 -0.0269 1.0000 0.0185
-11.750 -1.0792 0.03972 0.03402 -0.0251 1.0000 0.0189
-11.500 -1.0748 0.03815 0.03231 -0.0233 1.0000 0.0195
-11.250 -1.0675 0.03642 0.03038 -0.0217 1.0000 0.0202
-11.000 -1.0584 0.03459 0.02831 -0.0201 1.0000 0.0210
-10.750 -1.0470 0.03285 0.02628 -0.0187 1.0000 0.0222
-10.500 -1.0328 0.03137 0.02446 -0.0173 1.0000 0.0233
-10.250 -1.0185 0.02987 0.02289 -0.0162 1.0000 0.0244
-10.000 -1.0010 0.02888 0.02182 -0.0152 1.0000 0.0255
-9.750 -0.9828 0.02777 0.02058 -0.0142 1.0000 0.0268
-9.500 -0.9638 0.02669 0.01931 -0.0132 1.0000 0.0284
-9.250 -0.9435 0.02577 0.01815 -0.0123 1.0000 0.0300
-9.000 -0.9252 0.02440 0.01673 -0.0112 1.0000 0.0315
-8.750 -0.9047 0.02353 0.01578 -0.0104 1.0000 0.0331
-8.500 -0.8834 0.02275 0.01491 -0.0096 1.0000 0.0350
-8.250 -0.8617 0.02197 0.01400 -0.0087 1.0000 0.0369
-8.000 -0.8393 0.02126 0.01313 -0.0079 1.0000 0.0384
-7.750 -0.8196 0.02016 0.01204 -0.0069 1.0000 0.0405
-7.500 -0.7978 0.01946 0.01130 -0.0060 1.0000 0.0425
-7.250 -0.7757 0.01880 0.01056 -0.0052 1.0000 0.0444
-7.000 -0.7534 0.01819 0.00987 -0.0043 1.0000 0.0466
-6.750 -0.7307 0.01765 0.00924 -0.0034 1.0000 0.0484
-6.500 -0.7100 0.01686 0.00845 -0.0023 1.0000 0.0509
-6.250 -0.6879 0.01629 0.00785 -0.0013 1.0000 0.0535
-6.000 -0.6654 0.01580 0.00730 -0.0004 1.0000 0.0568
-5.750 -0.6431 0.01531 0.00678 0.0006 1.0000 0.0613
-5.500 -0.6209 0.01481 0.00631 0.0015 1.0000 0.0680
-5.250 -0.5986 0.01434 0.00584 0.0025 1.0000 0.0772
-5.000 -0.5762 0.01388 0.00543 0.0034 1.0000 0.0913
-4.750 -0.5537 0.01344 0.00507 0.0043 1.0000 0.1108
-4.500 -0.5313 0.01300 0.00475 0.0052 1.0000 0.1350
-4.250 -0.5088 0.01259 0.00445 0.0061 1.0000 0.1637
-4.000 -0.4864 0.01219 0.00420 0.0069 1.0000 0.1994
-3.750 -0.4640 0.01178 0.00398 0.0077 1.0000 0.2397
-3.500 -0.4414 0.01142 0.00378 0.0085 1.0000 0.2819
-3.250 -0.4190 0.01103 0.00364 0.0093 1.0000 0.3356
-3.000 -0.3951 0.01064 0.00352 0.0098 0.9994 0.3958
-2.750 -0.3590 0.01029 0.00341 0.0078 0.9941 0.4540
-2.500 -0.3237 0.01001 0.00331 0.0061 0.9877 0.5006
-2.250 -0.2882 0.00975 0.00323 0.0044 0.9812 0.5479
-2.000 -0.2526 0.00949 0.00316 0.0028 0.9744 0.5969
-1.750 -0.2196 0.00927 0.00311 0.0019 0.9654 0.6409
-1.500 -0.1866 0.00908 0.00307 0.0010 0.9560 0.6798
-1.250 -0.1527 0.00891 0.00304 0.0001 0.9461 0.7175
-1.000 -0.1217 0.00877 0.00303 -0.0002 0.9331 0.7521
-0.750 -0.0908 0.00866 0.00302 -0.0003 0.9189 0.7843
-0.500 -0.0601 0.00858 0.00301 -0.0003 0.9030 0.8140
-0.250 -0.0298 0.00854 0.00301 -0.0002 0.8853 0.8409
0.000 0.0000 0.00852 0.00302 0.0000 0.8641 0.8642
0.250 0.0298 0.00854 0.00301 0.0002 0.8409 0.8853
0.500 0.0602 0.00858 0.00301 0.0003 0.8140 0.9030
0.750 0.0908 0.00866 0.00302 0.0003 0.7843 0.9189
1.000 0.1217 0.00877 0.00303 0.0002 0.7521 0.9331
1.250 0.1527 0.00891 0.00304 -0.0001 0.7175 0.9461
1.500 0.1866 0.00908 0.00307 -0.0010 0.6798 0.9560
1.750 0.2196 0.00927 0.00311 -0.0019 0.6408 0.9654
2.000 0.2526 0.00949 0.00316 -0.0028 0.5970 0.9744
2.250 0.2882 0.00975 0.00323 -0.0044 0.5479 0.9812
2.500 0.3237 0.01001 0.00331 -0.0061 0.5007 0.9877
2.750 0.3591 0.01029 0.00341 -0.0078 0.4541 0.9942
3.000 0.3951 0.01064 0.00352 -0.0098 0.3960 0.9994
3.250 0.4189 0.01103 0.00364 -0.0093 0.3357 1.0000
3.500 0.4413 0.01142 0.00378 -0.0085 0.2819 1.0000
3.750 0.4639 0.01178 0.00398 -0.0077 0.2397 1.0000
4.000 0.4864 0.01219 0.00420 -0.0069 0.1995 1.0000
4.250 0.5088 0.01259 0.00445 -0.0061 0.1638 1.0000
4.500 0.5313 0.01300 0.00474 -0.0052 0.1351 1.0000
4.750 0.5537 0.01344 0.00507 -0.0043 0.1108 1.0000
5.000 0.5761 0.01388 0.00543 -0.0034 0.0913 1.0000
5.250 0.5985 0.01434 0.00584 -0.0025 0.0772 1.0000
5.500 0.6209 0.01481 0.00631 -0.0015 0.0681 1.0000
5.750 0.6431 0.01531 0.00678 -0.0006 0.0613 1.0000
6.000 0.6654 0.01580 0.00730 0.0004 0.0568 1.0000
6.250 0.6879 0.01629 0.00784 0.0013 0.0535 1.0000
6.500 0.7100 0.01686 0.00845 0.0023 0.0509 1.0000
6.750 0.7307 0.01764 0.00923 0.0034 0.0484 1.0000
7.000 0.7534 0.01819 0.00987 0.0043 0.0466 1.0000
7.250 0.7758 0.01880 0.01056 0.0052 0.0444 1.0000
7.500 0.7979 0.01946 0.01130 0.0060 0.0425 1.0000
7.750 0.8196 0.02016 0.01204 0.0069 0.0404 1.0000
8.000 0.8394 0.02126 0.01313 0.0079 0.0384 1.0000
8.250 0.8617 0.02197 0.01400 0.0087 0.0369 1.0000
8.500 0.8835 0.02275 0.01491 0.0096 0.0350 1.0000
8.750 0.9048 0.02352 0.01577 0.0104 0.0331 1.0000
9.000 0.9252 0.02440 0.01672 0.0112 0.0315 1.0000
9.250 0.9435 0.02578 0.01815 0.0122 0.0300 1.0000
9.500 0.9639 0.02670 0.01931 0.0132 0.0284 1.0000
9.750 0.9829 0.02778 0.02058 0.0142 0.0268 1.0000
10.000 1.0011 0.02888 0.02182 0.0152 0.0255 1.0000
10.250 1.0186 0.02986 0.02288 0.0161 0.0244 1.0000
10.500 1.0330 0.03137 0.02446 0.0173 0.0233 1.0000
10.750 1.0472 0.03285 0.02628 0.0186 0.0222 1.0000
11.000 1.0586 0.03459 0.02831 0.0201 0.0210 1.0000
11.250 1.0677 0.03641 0.03037 0.0216 0.0202 1.0000
11.500 1.0751 0.03815 0.03231 0.0232 0.0195 1.0000
11.750 1.0796 0.03972 0.03403 0.0250 0.0189 1.0000
12.000 1.0822 0.04130 0.03571 0.0268 0.0185 1.0000
12.250 1.0830 0.04315 0.03766 0.0281 0.0181 1.0000
12.500 1.0786 0.04577 0.04041 0.0288 0.0178 1.0000
12.750 1.0670 0.04968 0.04459 0.0284 0.0175 1.0000
13.000 1.0516 0.05467 0.04988 0.0264 0.0173 1.0000
13.250 1.0329 0.06093 0.05641 0.0225 0.0172 1.0000
13.500 1.0107 0.06873 0.06445 0.0168 0.0172 1.0000
13.750 0.9846 0.07813 0.07405 0.0099 0.0173 1.0000
14.000 0.9545 0.08895 0.08503 0.0024 0.0176 1.0000
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