NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64A410 (naca64a410-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.9 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a410-il-1000000-n5.txt Download as CSV file: xf-naca64a410-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4812 0.13305 0.13132 -0.0188 1.0000 0.0039
-12.250 -0.4784 0.12882 0.12710 -0.0205 1.0000 0.0040
-11.250 -0.7945 0.02995 0.02738 -0.0830 0.9771 0.0046
-11.000 -0.7858 0.02547 0.02242 -0.0840 0.9666 0.0047
-10.750 -0.7694 0.02313 0.01977 -0.0841 0.9591 0.0048
-10.500 -0.7503 0.02141 0.01780 -0.0840 0.9525 0.0049
-10.250 -0.7321 0.01945 0.01554 -0.0838 0.9466 0.0051
-10.000 -0.7105 0.01821 0.01412 -0.0836 0.9413 0.0053
-9.750 -0.6869 0.01741 0.01320 -0.0834 0.9368 0.0055
-9.500 -0.6625 0.01674 0.01243 -0.0834 0.9324 0.0057
-9.250 -0.6377 0.01613 0.01171 -0.0833 0.9278 0.0059
-9.000 -0.6129 0.01551 0.01098 -0.0831 0.9236 0.0061
-8.750 -0.5879 0.01489 0.01024 -0.0830 0.9196 0.0064
-8.500 -0.5627 0.01427 0.00950 -0.0829 0.9148 0.0067
-8.250 -0.5374 0.01370 0.00882 -0.0828 0.9099 0.0070
-8.000 -0.5116 0.01323 0.00823 -0.0827 0.9055 0.0072
-7.750 -0.4860 0.01263 0.00753 -0.0826 0.9010 0.0076
-7.500 -0.4596 0.01226 0.00711 -0.0826 0.8967 0.0081
-7.000 -0.4062 0.01160 0.00635 -0.0826 0.8889 0.0089
-6.750 -0.3795 0.01123 0.00591 -0.0826 0.8846 0.0094
-6.500 -0.3528 0.01088 0.00548 -0.0825 0.8805 0.0098
-6.250 -0.3259 0.01058 0.00510 -0.0825 0.8766 0.0102
-6.000 -0.2990 0.01022 0.00469 -0.0825 0.8721 0.0106
-5.750 -0.2726 0.00979 0.00421 -0.0824 0.8675 0.0115
-5.500 -0.2456 0.00957 0.00395 -0.0824 0.8621 0.0122
-5.250 -0.2186 0.00931 0.00364 -0.0823 0.8538 0.0128
-5.000 -0.1917 0.00907 0.00333 -0.0823 0.8463 0.0134
-4.750 -0.1643 0.00885 0.00306 -0.0823 0.8398 0.0140
-4.500 -0.1370 0.00868 0.00283 -0.0822 0.8335 0.0145
-4.250 -0.1098 0.00837 0.00247 -0.0822 0.8260 0.0157
-4.000 -0.0825 0.00817 0.00223 -0.0822 0.8178 0.0168
-3.750 -0.0551 0.00801 0.00203 -0.0822 0.8078 0.0179
-3.500 -0.0276 0.00787 0.00184 -0.0821 0.7973 0.0193
-3.250 -0.0003 0.00774 0.00166 -0.0821 0.7858 0.0218
-3.000 0.0268 0.00764 0.00153 -0.0820 0.7723 0.0262
-2.750 0.0539 0.00756 0.00140 -0.0819 0.7571 0.0316
-2.500 0.0809 0.00751 0.00129 -0.0818 0.7425 0.0370
-2.250 0.1081 0.00746 0.00119 -0.0817 0.7283 0.0435
-2.000 0.1351 0.00744 0.00111 -0.0816 0.7118 0.0490
-1.500 0.1894 0.00727 0.00101 -0.0815 0.6874 0.1029
-1.250 0.2169 0.00729 0.00098 -0.0815 0.6749 0.1080
-1.000 0.2444 0.00729 0.00094 -0.0815 0.6611 0.1122
-0.750 0.2716 0.00730 0.00090 -0.0815 0.6457 0.1165
-0.500 0.2988 0.00733 0.00089 -0.0814 0.6298 0.1202
-0.250 0.3261 0.00737 0.00088 -0.0813 0.6148 0.1240
0.000 0.3532 0.00740 0.00088 -0.0813 0.5989 0.1316
0.250 0.3773 0.00658 0.00084 -0.0813 0.5827 0.4293
0.500 0.4035 0.00645 0.00088 -0.0811 0.5649 0.5091
0.750 0.4299 0.00644 0.00094 -0.0810 0.5456 0.5591
1.000 0.4553 0.00664 0.00103 -0.0807 0.5050 0.5816
1.250 0.4783 0.00709 0.00120 -0.0800 0.4245 0.6008
1.500 0.4904 0.00885 0.00182 -0.0777 0.1376 0.6157
1.750 0.5170 0.00899 0.00194 -0.0776 0.1230 0.6328
2.000 0.5440 0.00907 0.00205 -0.0776 0.1191 0.6497
2.250 0.5709 0.00918 0.00217 -0.0775 0.1138 0.6663
2.500 0.5978 0.00926 0.00230 -0.0774 0.1103 0.6851
2.750 0.6248 0.00934 0.00243 -0.0773 0.1092 0.7022
3.000 0.6517 0.00943 0.00257 -0.0773 0.1064 0.7169
3.250 0.6780 0.00959 0.00273 -0.0771 0.0995 0.7318
3.500 0.7047 0.00970 0.00288 -0.0770 0.0959 0.7466
3.750 0.7314 0.00980 0.00302 -0.0769 0.0894 0.7609
4.000 0.7557 0.01016 0.00323 -0.0765 0.0514 0.7754
4.250 0.7813 0.01035 0.00345 -0.0762 0.0441 0.7911
4.500 0.8068 0.01050 0.00367 -0.0759 0.0390 0.8092
4.750 0.8314 0.01062 0.00391 -0.0753 0.0338 0.8406
5.000 0.8595 0.01064 0.00416 -0.0755 0.0270 1.0000
5.250 0.8844 0.01095 0.00442 -0.0751 0.0204 1.0000
5.500 0.9091 0.01126 0.00470 -0.0747 0.0162 1.0000
5.750 0.9340 0.01155 0.00500 -0.0743 0.0143 1.0000
6.000 0.9587 0.01185 0.00531 -0.0739 0.0132 1.0000
6.250 0.9831 0.01218 0.00565 -0.0735 0.0123 1.0000
6.500 1.0071 0.01255 0.00603 -0.0729 0.0115 1.0000
6.750 1.0304 0.01298 0.00650 -0.0723 0.0109 1.0000
7.000 1.0536 0.01339 0.00695 -0.0717 0.0106 1.0000
7.250 1.0770 0.01378 0.00738 -0.0710 0.0104 1.0000
7.500 1.0999 0.01421 0.00785 -0.0704 0.0101 1.0000
7.750 1.1225 0.01464 0.00832 -0.0697 0.0098 1.0000
8.000 1.1448 0.01509 0.00882 -0.0689 0.0094 1.0000
8.250 1.1664 0.01558 0.00936 -0.0681 0.0092 1.0000
8.500 1.1875 0.01610 0.00993 -0.0672 0.0089 1.0000
8.750 1.2081 0.01665 0.01052 -0.0662 0.0087 1.0000
9.000 1.2283 0.01721 0.01112 -0.0652 0.0084 1.0000
9.250 1.2479 0.01779 0.01175 -0.0641 0.0081 1.0000
9.500 1.2656 0.01851 0.01254 -0.0627 0.0078 1.0000
9.750 1.2790 0.01949 0.01360 -0.0606 0.0075 1.0000
10.000 1.2928 0.02039 0.01459 -0.0586 0.0073 1.0000
10.250 1.3092 0.02103 0.01530 -0.0570 0.0072 1.0000
10.500 1.3250 0.02171 0.01605 -0.0554 0.0071 1.0000
10.750 1.3405 0.02241 0.01683 -0.0539 0.0070 1.0000
11.000 1.3558 0.02311 0.01760 -0.0523 0.0068 1.0000
11.250 1.3706 0.02385 0.01843 -0.0508 0.0066 1.0000
11.500 1.3844 0.02467 0.01932 -0.0492 0.0064 1.0000
11.750 1.3980 0.02550 0.02023 -0.0477 0.0062 1.0000
12.000 1.4106 0.02642 0.02123 -0.0461 0.0060 1.0000
12.250 1.4229 0.02736 0.02224 -0.0445 0.0058 1.0000
12.500 1.4347 0.02836 0.02331 -0.0430 0.0057 1.0000
12.750 1.4462 0.02939 0.02441 -0.0416 0.0055 1.0000
13.000 1.4568 0.03050 0.02559 -0.0401 0.0054 1.0000
13.250 1.4658 0.03178 0.02695 -0.0386 0.0052 1.0000
13.500 1.4717 0.03336 0.02864 -0.0369 0.0051 1.0000
13.750 1.4714 0.03557 0.03098 -0.0350 0.0049 1.0000
14.000 1.4777 0.03721 0.03273 -0.0336 0.0049 1.0000
14.250 1.4829 0.03898 0.03462 -0.0324 0.0048 1.0000
14.500 1.4878 0.04084 0.03659 -0.0313 0.0047 1.0000
14.750 1.4911 0.04291 0.03878 -0.0304 0.0046 1.0000
15.000 1.4938 0.04510 0.04109 -0.0295 0.0045 1.0000
15.250 1.4945 0.04758 0.04370 -0.0288 0.0044 1.0000
15.500 1.4945 0.05023 0.04647 -0.0283 0.0043 1.0000
15.750 1.4926 0.05317 0.04952 -0.0280 0.0042 1.0000
16.000 1.4915 0.05614 0.05261 -0.0280 0.0041 1.0000
16.250 1.4885 0.05952 0.05611 -0.0282 0.0040 1.0000
16.500 1.4836 0.06327 0.05998 -0.0287 0.0039 1.0000
16.750 1.4781 0.06726 0.06410 -0.0295 0.0038 1.0000
17.000 1.4704 0.07176 0.06872 -0.0306 0.0038 1.0000
17.250 1.4611 0.07669 0.07378 -0.0322 0.0037 1.0000
17.500 1.4478 0.08244 0.07967 -0.0343 0.0037 1.0000
17.750 1.4311 0.08906 0.08644 -0.0370 0.0036 1.0000
18.000 1.4085 0.09713 0.09467 -0.0407 0.0036 1.0000
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