NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0010-64 (naca001064-il) Reynolds number: 200,000 Max Cl/Cd: 38.68 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001064-il-200000-n5.txt Download as CSV file: xf-naca001064-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.8682 0.07191 0.06803 -0.0302 1.0000 0.0184
-12.500 -0.8976 0.06310 0.05903 -0.0366 1.0000 0.0182
-12.250 -0.9261 0.05644 0.05213 -0.0394 1.0000 0.0181
-12.000 -0.9523 0.05117 0.04656 -0.0394 1.0000 0.0182
-11.750 -0.9756 0.04680 0.04185 -0.0373 1.0000 0.0184
-11.500 -0.9943 0.04317 0.03782 -0.0338 1.0000 0.0188
-11.250 -1.0037 0.04041 0.03476 -0.0302 1.0000 0.0191
-11.000 -0.9988 0.03886 0.03310 -0.0280 1.0000 0.0196
-10.750 -0.9902 0.03762 0.03176 -0.0261 1.0000 0.0201
-10.500 -0.9807 0.03630 0.03030 -0.0242 1.0000 0.0208
-10.250 -0.9705 0.03493 0.02873 -0.0222 1.0000 0.0217
-10.000 -0.9602 0.03332 0.02684 -0.0201 1.0000 0.0229
-9.750 -0.9490 0.03159 0.02477 -0.0179 1.0000 0.0243
-9.500 -0.9358 0.03012 0.02296 -0.0158 1.0000 0.0253
-9.250 -0.9225 0.02843 0.02113 -0.0141 1.0000 0.0264
-9.000 -0.9062 0.02762 0.02027 -0.0125 1.0000 0.0276
-8.750 -0.8896 0.02684 0.01938 -0.0108 1.0000 0.0290
-8.500 -0.8727 0.02588 0.01824 -0.0091 1.0000 0.0306
-8.250 -0.8550 0.02488 0.01702 -0.0075 1.0000 0.0320
-8.000 -0.8367 0.02410 0.01606 -0.0059 1.0000 0.0332
-7.750 -0.8197 0.02276 0.01465 -0.0043 1.0000 0.0349
-7.500 -0.8016 0.02202 0.01387 -0.0028 1.0000 0.0363
-7.250 -0.7830 0.02132 0.01309 -0.0012 1.0000 0.0378
-7.000 -0.7642 0.02067 0.01236 0.0004 1.0000 0.0395
-6.750 -0.7453 0.02002 0.01160 0.0019 1.0000 0.0410
-6.500 -0.7264 0.01938 0.01084 0.0035 1.0000 0.0420
-6.250 -0.7084 0.01863 0.01005 0.0052 1.0000 0.0432
-6.000 -0.6910 0.01791 0.00933 0.0070 1.0000 0.0451
-5.750 -0.6725 0.01740 0.00879 0.0086 1.0000 0.0469
-5.500 -0.6537 0.01691 0.00826 0.0102 1.0000 0.0485
-5.250 -0.6347 0.01645 0.00774 0.0117 1.0000 0.0501
-5.000 -0.6154 0.01603 0.00727 0.0132 1.0000 0.0519
-4.750 -0.5866 0.01557 0.00676 0.0127 0.9979 0.0543
-4.500 -0.5551 0.01509 0.00630 0.0115 0.9951 0.0592
-4.250 -0.5235 0.01472 0.00590 0.0104 0.9921 0.0664
-4.000 -0.4923 0.01429 0.00551 0.0094 0.9887 0.0790
-3.750 -0.4603 0.01384 0.00517 0.0081 0.9858 0.1005
-3.500 -0.4300 0.01339 0.00487 0.0071 0.9822 0.1347
-3.250 -0.4000 0.01291 0.00461 0.0062 0.9782 0.1842
-3.000 -0.3687 0.01236 0.00436 0.0049 0.9750 0.2518
-2.750 -0.3427 0.01157 0.00409 0.0047 0.9704 0.3688
-2.500 -0.3203 0.01052 0.00393 0.0053 0.9655 0.5595
-2.250 -0.2922 0.01001 0.00401 0.0055 0.9625 0.6917
-2.000 -0.2640 0.00987 0.00409 0.0059 0.9578 0.7561
-1.750 -0.2328 0.00983 0.00414 0.0055 0.9533 0.7911
-1.250 -0.1649 0.00993 0.00435 0.0038 0.9470 0.8553
-1.000 -0.1359 0.01006 0.00451 0.0042 0.9408 0.8786
-0.750 -0.1016 0.01018 0.00464 0.0033 0.9365 0.8964
-0.500 -0.0651 0.01022 0.00466 0.0017 0.9331 0.9062
-0.250 -0.0352 0.01024 0.00468 0.0014 0.9257 0.9145
0.000 0.0000 0.01024 0.00467 0.0000 0.9204 0.9204
0.250 0.0352 0.01024 0.00468 -0.0014 0.9144 0.9257
0.500 0.0651 0.01022 0.00466 -0.0017 0.9062 0.9331
0.750 0.1016 0.01018 0.00464 -0.0033 0.8964 0.9365
1.000 0.1359 0.01006 0.00451 -0.0042 0.8786 0.9408
1.250 0.1649 0.00993 0.00435 -0.0038 0.8553 0.9470
1.750 0.2328 0.00983 0.00414 -0.0055 0.7910 0.9533
2.000 0.2640 0.00987 0.00409 -0.0059 0.7561 0.9578
2.250 0.2922 0.01001 0.00401 -0.0055 0.6913 0.9625
2.500 0.3202 0.01053 0.00393 -0.0053 0.5584 0.9655
2.750 0.3427 0.01157 0.00409 -0.0047 0.3690 0.9705
3.000 0.3687 0.01236 0.00436 -0.0050 0.2519 0.9751
3.250 0.4000 0.01291 0.00461 -0.0062 0.1843 0.9782
3.500 0.4300 0.01339 0.00487 -0.0071 0.1347 0.9822
3.750 0.4603 0.01383 0.00517 -0.0081 0.1005 0.9858
4.000 0.4924 0.01429 0.00551 -0.0094 0.0790 0.9888
4.250 0.5235 0.01472 0.00589 -0.0104 0.0663 0.9921
4.500 0.5552 0.01509 0.00630 -0.0115 0.0592 0.9952
4.750 0.5867 0.01557 0.00676 -0.0127 0.0543 0.9979
5.000 0.6153 0.01603 0.00727 -0.0132 0.0519 1.0000
5.250 0.6347 0.01645 0.00774 -0.0117 0.0501 1.0000
5.500 0.6537 0.01690 0.00826 -0.0102 0.0485 1.0000
5.750 0.6724 0.01739 0.00879 -0.0086 0.0469 1.0000
6.000 0.6910 0.01790 0.00932 -0.0070 0.0451 1.0000
6.250 0.7083 0.01863 0.01004 -0.0052 0.0432 1.0000
6.500 0.7264 0.01937 0.01084 -0.0035 0.0420 1.0000
6.750 0.7453 0.02002 0.01160 -0.0019 0.0410 1.0000
7.000 0.7642 0.02067 0.01236 -0.0003 0.0395 1.0000
7.250 0.7830 0.02132 0.01309 0.0012 0.0378 1.0000
7.500 0.8015 0.02202 0.01387 0.0028 0.0363 1.0000
7.750 0.8197 0.02275 0.01464 0.0043 0.0349 1.0000
8.000 0.8367 0.02410 0.01605 0.0059 0.0332 1.0000
8.250 0.8550 0.02488 0.01702 0.0075 0.0320 1.0000
8.500 0.8727 0.02588 0.01824 0.0091 0.0306 1.0000
8.750 0.8896 0.02684 0.01937 0.0108 0.0290 1.0000
9.000 0.9062 0.02763 0.02027 0.0125 0.0276 1.0000
9.250 0.9225 0.02843 0.02113 0.0140 0.0264 1.0000
9.500 0.9359 0.03012 0.02296 0.0158 0.0253 1.0000
9.750 0.9491 0.03159 0.02477 0.0179 0.0243 1.0000
10.000 0.9603 0.03332 0.02685 0.0201 0.0229 1.0000
10.250 0.9707 0.03492 0.02872 0.0222 0.0217 1.0000
10.500 0.9809 0.03631 0.03030 0.0241 0.0207 1.0000
10.750 0.9903 0.03763 0.03177 0.0261 0.0201 1.0000
11.000 0.9990 0.03886 0.03311 0.0280 0.0196 1.0000
11.250 1.0040 0.04041 0.03476 0.0302 0.0191 1.0000
11.500 0.9946 0.04319 0.03785 0.0338 0.0187 1.0000
11.750 0.9760 0.04683 0.04188 0.0373 0.0184 1.0000
12.000 0.9527 0.05121 0.04661 0.0393 0.0182 1.0000
12.250 0.9261 0.05654 0.05223 0.0393 0.0181 1.0000
12.500 0.8978 0.06323 0.05917 0.0363 0.0182 1.0000
12.750 0.8683 0.07213 0.06827 0.0299 0.0184 1.0000
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Polar data table (+)
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