NACA 0012-64 (naca001264-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0012-64 (naca001264-il) Reynolds number: 100,000 Max Cl/Cd: 32.2 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001264-il-100000-n5.txt Download as CSV file: xf-naca001264-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-64
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7594 0.08725 0.08155 -0.0367 1.0000 0.0445
-12.500 -0.8158 0.07417 0.06826 -0.0454 1.0000 0.0436
-12.250 -0.8538 0.06691 0.06076 -0.0479 1.0000 0.0433
-12.000 -0.8824 0.06190 0.05553 -0.0476 1.0000 0.0433
-11.750 -0.9053 0.05803 0.05140 -0.0456 1.0000 0.0435
-11.500 -0.9245 0.05480 0.04793 -0.0425 1.0000 0.0439
-11.250 -0.9408 0.05201 0.04487 -0.0384 1.0000 0.0443
-11.000 -0.9520 0.04924 0.04179 -0.0345 1.0000 0.0448
-10.750 -0.9583 0.04654 0.03873 -0.0309 1.0000 0.0455
-10.500 -0.9616 0.04409 0.03587 -0.0272 1.0000 0.0465
-10.250 -0.9618 0.04190 0.03326 -0.0236 1.0000 0.0475
-10.000 -0.9504 0.04017 0.03149 -0.0218 1.0000 0.0485
-9.750 -0.9395 0.03872 0.02993 -0.0197 1.0000 0.0495
-9.500 -0.9281 0.03720 0.02823 -0.0175 1.0000 0.0505
-9.250 -0.9156 0.03569 0.02653 -0.0153 1.0000 0.0515
-9.000 -0.9024 0.03434 0.02497 -0.0131 1.0000 0.0531
-8.750 -0.8881 0.03303 0.02342 -0.0111 1.0000 0.0548
-8.500 -0.8723 0.03174 0.02186 -0.0091 1.0000 0.0562
-8.250 -0.8545 0.03037 0.02037 -0.0076 1.0000 0.0574
-8.000 -0.8370 0.02919 0.01918 -0.0061 1.0000 0.0587
-7.750 -0.8198 0.02821 0.01814 -0.0044 1.0000 0.0601
-7.500 -0.8029 0.02734 0.01722 -0.0026 1.0000 0.0621
-7.250 -0.7859 0.02653 0.01631 -0.0008 1.0000 0.0646
-7.000 -0.7685 0.02574 0.01539 0.0010 1.0000 0.0670
-6.750 -0.7522 0.02483 0.01446 0.0029 1.0000 0.0691
-6.500 -0.7368 0.02405 0.01370 0.0049 1.0000 0.0715
-6.250 -0.7212 0.02336 0.01299 0.0070 1.0000 0.0745
-6.000 -0.7054 0.02272 0.01228 0.0091 1.0000 0.0781
-5.750 -0.6906 0.02204 0.01161 0.0113 1.0000 0.0826
-5.500 -0.6751 0.02146 0.01103 0.0133 1.0000 0.0890
-5.250 -0.6594 0.02087 0.01046 0.0153 1.0000 0.0966
-5.000 -0.6430 0.02035 0.00993 0.0172 1.0000 0.1067
-4.750 -0.6265 0.01980 0.00946 0.0191 1.0000 0.1195
-4.500 -0.6094 0.01930 0.00904 0.0208 1.0000 0.1381
-4.250 -0.5921 0.01879 0.00868 0.0224 1.0000 0.1659
-4.000 -0.5694 0.01818 0.00832 0.0227 0.9983 0.2109
-3.750 -0.5415 0.01729 0.00794 0.0218 0.9946 0.2987
-3.500 -0.5188 0.01612 0.00769 0.0221 0.9904 0.4614
-3.250 -0.4930 0.01553 0.00784 0.0228 0.9866 0.6114
-3.000 -0.4604 0.01552 0.00808 0.0224 0.9833 0.6925
-2.750 -0.4296 0.01562 0.00826 0.0223 0.9786 0.7419
-2.500 -0.3952 0.01583 0.00849 0.0215 0.9746 0.7803
-2.250 -0.3603 0.01614 0.00879 0.0207 0.9710 0.8151
-2.000 -0.3272 0.01647 0.00910 0.0203 0.9661 0.8422
-1.750 -0.2910 0.01679 0.00935 0.0191 0.9621 0.8641
-1.500 -0.2484 0.01729 0.00982 0.0169 0.9598 0.8850
-1.250 -0.2077 0.01770 0.01017 0.0148 0.9562 0.9009
-1.000 -0.1691 0.01786 0.01027 0.0126 0.9512 0.9107
-0.750 -0.1256 0.01795 0.01031 0.0093 0.9476 0.9166
-0.500 -0.0789 0.01803 0.01035 0.0052 0.9448 0.9216
-0.250 -0.0476 0.01805 0.01035 0.0043 0.9372 0.9300
0.000 0.0000 0.01807 0.01037 0.0000 0.9333 0.9333
0.250 0.0475 0.01805 0.01035 -0.0043 0.9300 0.9372
0.500 0.0789 0.01803 0.01035 -0.0052 0.9216 0.9448
0.750 0.1256 0.01795 0.01031 -0.0093 0.9166 0.9476
1.000 0.1691 0.01786 0.01027 -0.0127 0.9107 0.9512
1.250 0.2076 0.01770 0.01016 -0.0148 0.9009 0.9562
1.500 0.2483 0.01729 0.00982 -0.0169 0.8850 0.9598
1.750 0.2910 0.01679 0.00935 -0.0191 0.8642 0.9621
2.000 0.3272 0.01647 0.00909 -0.0203 0.8422 0.9661
2.250 0.3603 0.01614 0.00878 -0.0207 0.8152 0.9711
2.500 0.3952 0.01583 0.00849 -0.0215 0.7804 0.9746
2.750 0.4296 0.01562 0.00826 -0.0223 0.7421 0.9786
3.000 0.4603 0.01552 0.00807 -0.0224 0.6925 0.9833
3.250 0.4930 0.01553 0.00784 -0.0228 0.6115 0.9866
3.500 0.5188 0.01611 0.00769 -0.0221 0.4615 0.9905
3.750 0.5415 0.01729 0.00794 -0.0219 0.2985 0.9946
4.000 0.5694 0.01817 0.00832 -0.0228 0.2109 0.9984
4.250 0.5920 0.01878 0.00868 -0.0223 0.1660 1.0000
4.500 0.6093 0.01929 0.00904 -0.0207 0.1381 1.0000
4.750 0.6264 0.01979 0.00946 -0.0190 0.1195 1.0000
5.000 0.6429 0.02034 0.00992 -0.0172 0.1068 1.0000
5.250 0.6593 0.02087 0.01045 -0.0153 0.0967 1.0000
5.500 0.6750 0.02146 0.01103 -0.0133 0.0890 1.0000
5.750 0.6905 0.02203 0.01161 -0.0112 0.0826 1.0000
6.000 0.7053 0.02271 0.01228 -0.0091 0.0781 1.0000
6.250 0.7211 0.02336 0.01299 -0.0070 0.0745 1.0000
6.500 0.7367 0.02405 0.01370 -0.0049 0.0715 1.0000
6.750 0.7521 0.02483 0.01446 -0.0029 0.0691 1.0000
7.000 0.7684 0.02574 0.01539 -0.0010 0.0670 1.0000
7.250 0.7858 0.02652 0.01631 0.0009 0.0646 1.0000
7.500 0.8029 0.02733 0.01721 0.0027 0.0621 1.0000
7.750 0.8197 0.02820 0.01814 0.0044 0.0601 1.0000
8.000 0.8369 0.02919 0.01918 0.0061 0.0587 1.0000
8.250 0.8545 0.03036 0.02036 0.0076 0.0574 1.0000
8.500 0.8723 0.03173 0.02186 0.0091 0.0562 1.0000
8.750 0.8880 0.03302 0.02342 0.0111 0.0548 1.0000
9.000 0.9023 0.03434 0.02496 0.0132 0.0531 1.0000
9.250 0.9156 0.03568 0.02653 0.0153 0.0515 1.0000
9.500 0.9281 0.03719 0.02823 0.0175 0.0505 1.0000
9.750 0.9395 0.03872 0.02993 0.0197 0.0495 1.0000
10.000 0.9505 0.04016 0.03148 0.0218 0.0485 1.0000
10.250 0.9619 0.04190 0.03326 0.0236 0.0475 1.0000
10.500 0.9618 0.04409 0.03587 0.0272 0.0465 1.0000
10.750 0.9584 0.04655 0.03874 0.0309 0.0455 1.0000
11.000 0.9522 0.04925 0.04180 0.0345 0.0448 1.0000
11.250 0.9412 0.05202 0.04489 0.0383 0.0443 1.0000
11.500 0.9249 0.05483 0.04796 0.0424 0.0439 1.0000
11.750 0.9058 0.05805 0.05143 0.0455 0.0435 1.0000
12.000 0.8829 0.06194 0.05557 0.0474 0.0433 1.0000
12.250 0.8543 0.06698 0.06083 0.0477 0.0433 1.0000
12.500 0.8162 0.07428 0.06837 0.0451 0.0436 1.0000
12.750 0.7593 0.08756 0.08187 0.0363 0.0446 1.0000
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