NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64A410 (naca64a410-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.63 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64a410-il-1000000.txt Download as CSV file: xf-naca64a410-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A410
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3298 0.09418 0.09264 -0.0417 1.0000 0.0114
-10.250 -0.3324 0.09049 0.08897 -0.0422 1.0000 0.0117
-10.000 -0.4436 0.09566 0.09403 -0.0368 1.0000 0.0105
-9.750 -0.4400 0.09225 0.09063 -0.0385 1.0000 0.0107
-9.500 -0.4373 0.08862 0.08702 -0.0404 1.0000 0.0110
-9.250 -0.4365 0.08474 0.08316 -0.0425 1.0000 0.0113
-9.000 -0.4411 0.08106 0.07951 -0.0437 1.0000 0.0117
-8.000 -0.4543 0.02912 0.02633 -0.0893 0.9572 0.0095
-7.750 -0.4453 0.02309 0.01964 -0.0888 0.9495 0.0097
-7.500 -0.4339 0.01792 0.01378 -0.0880 0.9433 0.0104
-7.250 -0.4097 0.01712 0.01287 -0.0878 0.9390 0.0108
-7.000 -0.3852 0.01631 0.01194 -0.0876 0.9344 0.0112
-6.750 -0.3608 0.01536 0.01082 -0.0872 0.9302 0.0117
-6.500 -0.3359 0.01432 0.00960 -0.0869 0.9262 0.0122
-6.250 -0.3107 0.01340 0.00854 -0.0866 0.9217 0.0127
-6.000 -0.2849 0.01273 0.00776 -0.0863 0.9174 0.0132
-5.750 -0.2594 0.01192 0.00680 -0.0860 0.9133 0.0138
-5.500 -0.2348 0.01092 0.00573 -0.0857 0.9090 0.0149
-5.250 -0.2083 0.01054 0.00531 -0.0855 0.9044 0.0157
-5.000 -0.1819 0.01011 0.00482 -0.0853 0.9002 0.0165
-4.750 -0.1553 0.00969 0.00434 -0.0851 0.8955 0.0172
-4.500 -0.1288 0.00935 0.00394 -0.0849 0.8891 0.0180
-4.250 -0.1029 0.00884 0.00333 -0.0846 0.8828 0.0192
-4.000 -0.0762 0.00845 0.00292 -0.0844 0.8773 0.0211
-3.750 -0.0490 0.00822 0.00265 -0.0844 0.8720 0.0226
-3.500 -0.0216 0.00803 0.00241 -0.0843 0.8668 0.0243
-3.250 0.0055 0.00772 0.00205 -0.0842 0.8605 0.0278
-3.000 0.0329 0.00758 0.00189 -0.0841 0.8542 0.0328
-2.750 0.0602 0.00734 0.00166 -0.0840 0.8463 0.0418
-2.500 0.0877 0.00720 0.00147 -0.0840 0.8394 0.0510
-2.250 0.1150 0.00694 0.00135 -0.0840 0.8314 0.0933
-2.000 0.1426 0.00685 0.00127 -0.0840 0.8238 0.1119
-1.750 0.1703 0.00676 0.00117 -0.0840 0.8145 0.1218
-1.500 0.1977 0.00665 0.00107 -0.0839 0.8030 0.1343
-1.250 0.2240 0.00629 0.00096 -0.0839 0.7917 0.2295
-1.000 0.2488 0.00563 0.00085 -0.0837 0.7803 0.4276
-0.750 0.2750 0.00541 0.00083 -0.0836 0.7682 0.5166
-0.500 0.3019 0.00533 0.00083 -0.0834 0.7561 0.5612
-0.250 0.3289 0.00527 0.00085 -0.0833 0.7444 0.6036
0.000 0.3558 0.00523 0.00089 -0.0831 0.7331 0.6441
0.250 0.3828 0.00524 0.00092 -0.0830 0.7216 0.6703
0.500 0.4098 0.00525 0.00096 -0.0828 0.7101 0.6958
0.750 0.4369 0.00528 0.00100 -0.0827 0.6983 0.7147
1.000 0.4642 0.00533 0.00104 -0.0826 0.6851 0.7291
1.250 0.4905 0.00542 0.00109 -0.0823 0.6609 0.7432
1.500 0.5162 0.00556 0.00114 -0.0819 0.6297 0.7569
1.750 0.5420 0.00571 0.00121 -0.0815 0.6006 0.7706
2.000 0.5679 0.00586 0.00129 -0.0812 0.5722 0.7850
2.250 0.5929 0.00604 0.00139 -0.0807 0.5365 0.8029
2.500 0.6174 0.00626 0.00152 -0.0801 0.4947 0.8222
2.750 0.6394 0.00654 0.00169 -0.0791 0.4335 0.8575
3.000 0.6643 0.00760 0.00220 -0.0792 0.2570 1.0000
3.250 0.6833 0.00852 0.00260 -0.0780 0.1410 1.0000
3.500 0.7086 0.00881 0.00281 -0.0777 0.1243 1.0000
3.750 0.7344 0.00906 0.00300 -0.0774 0.1151 1.0000
4.000 0.7609 0.00922 0.00317 -0.0773 0.1102 1.0000
4.250 0.7868 0.00944 0.00336 -0.0771 0.1029 1.0000
4.500 0.8131 0.00962 0.00353 -0.0769 0.0924 1.0000
4.750 0.8362 0.01012 0.00380 -0.0763 0.0500 1.0000
5.000 0.8607 0.01049 0.00414 -0.0758 0.0398 1.0000
5.250 0.8859 0.01078 0.00442 -0.0755 0.0331 1.0000
5.500 0.9100 0.01118 0.00478 -0.0749 0.0246 1.0000
5.750 0.9337 0.01162 0.00522 -0.0743 0.0201 1.0000
6.000 0.9581 0.01196 0.00558 -0.0738 0.0183 1.0000
6.250 0.9815 0.01241 0.00603 -0.0732 0.0164 1.0000
6.500 1.0030 0.01306 0.00675 -0.0721 0.0151 1.0000
6.750 1.0264 0.01348 0.00721 -0.0715 0.0146 1.0000
7.000 1.0490 0.01397 0.00775 -0.0707 0.0140 1.0000
7.250 1.0709 0.01451 0.00833 -0.0698 0.0135 1.0000
7.500 1.0923 0.01508 0.00895 -0.0689 0.0130 1.0000
7.750 1.1133 0.01568 0.00961 -0.0679 0.0126 1.0000
8.000 1.1335 0.01633 0.01030 -0.0668 0.0122 1.0000
8.250 1.1515 0.01719 0.01121 -0.0654 0.0116 1.0000
8.500 1.1609 0.01915 0.01330 -0.0626 0.0109 1.0000
8.750 1.1817 0.01972 0.01394 -0.0616 0.0107 1.0000
9.000 1.2011 0.02046 0.01475 -0.0604 0.0105 1.0000
9.250 1.2196 0.02134 0.01573 -0.0591 0.0102 1.0000
9.500 1.2370 0.02234 0.01682 -0.0577 0.0100 1.0000
9.750 1.2535 0.02341 0.01799 -0.0561 0.0097 1.0000
10.000 1.2696 0.02440 0.01908 -0.0546 0.0094 1.0000
10.250 1.2848 0.02526 0.02001 -0.0529 0.0091 1.0000
10.500 1.2991 0.02603 0.02086 -0.0512 0.0088 1.0000
10.750 1.3124 0.02685 0.02174 -0.0494 0.0085 1.0000
11.000 1.3240 0.02792 0.02289 -0.0475 0.0083 1.0000
11.250 1.3328 0.02946 0.02454 -0.0454 0.0081 1.0000
11.500 1.3257 0.03423 0.02970 -0.0416 0.0077 1.0000
11.750 1.3290 0.03584 0.03149 -0.0390 0.0076 1.0000
12.000 1.3338 0.03724 0.03303 -0.0368 0.0075 1.0000
12.250 1.3359 0.03905 0.03500 -0.0346 0.0073 1.0000
12.500 1.3344 0.04132 0.03746 -0.0323 0.0072 1.0000
12.750 1.3302 0.04394 0.04027 -0.0302 0.0071 1.0000
13.000 1.3218 0.04711 0.04366 -0.0282 0.0070 1.0000
13.250 1.3105 0.05072 0.04747 -0.0266 0.0069 1.0000
13.500 1.2958 0.05494 0.05191 -0.0255 0.0068 1.0000
13.750 1.2783 0.05975 0.05693 -0.0251 0.0068 1.0000
14.000 1.2588 0.06519 0.06257 -0.0256 0.0067 1.0000
14.250 1.2349 0.07168 0.06927 -0.0271 0.0067 1.0000
14.500 1.2092 0.07920 0.07698 -0.0298 0.0068 1.0000
14.750 1.1810 0.08796 0.08594 -0.0339 0.0068 1.0000
15.000 1.1498 0.09855 0.09671 -0.0399 0.0069 1.0000
15.250 1.1168 0.11119 0.10952 -0.0478 0.0070 1.0000
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