NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0010-64 (naca001064-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.59 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca001064-il-1000000-n5.txt Download as CSV file: xf-naca001064-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.8854 0.16122 0.15940 0.0235 1.0000 0.0064
-17.500 -1.0072 0.12778 0.12571 0.0059 1.0000 0.0059
-17.250 -1.2933 0.06451 0.06168 -0.0304 1.0000 0.0049
-17.000 -1.3230 0.05569 0.05265 -0.0359 1.0000 0.0049
-16.750 -1.3412 0.04980 0.04658 -0.0388 1.0000 0.0049
-16.500 -1.3533 0.04534 0.04196 -0.0402 1.0000 0.0049
-16.250 -1.3617 0.04175 0.03823 -0.0406 1.0000 0.0050
-16.000 -1.3666 0.03882 0.03515 -0.0403 1.0000 0.0050
-15.750 -1.3692 0.03634 0.03254 -0.0396 1.0000 0.0051
-15.500 -1.3694 0.03424 0.03031 -0.0384 1.0000 0.0052
-15.250 -1.3679 0.03240 0.02834 -0.0369 1.0000 0.0053
-15.000 -1.3645 0.03079 0.02661 -0.0352 1.0000 0.0053
-14.750 -1.3594 0.02938 0.02508 -0.0334 1.0000 0.0054
-14.500 -1.3528 0.02814 0.02372 -0.0314 1.0000 0.0055
-14.250 -1.3449 0.02700 0.02248 -0.0294 1.0000 0.0056
-14.000 -1.3387 0.02575 0.02112 -0.0270 1.0000 0.0058
-13.750 -1.3302 0.02469 0.01995 -0.0247 1.0000 0.0060
-13.500 -1.3196 0.02376 0.01894 -0.0225 1.0000 0.0063
-13.250 -1.3059 0.02291 0.01801 -0.0208 1.0000 0.0065
-13.000 -1.2905 0.02211 0.01712 -0.0193 1.0000 0.0068
-12.750 -1.2740 0.02136 0.01629 -0.0179 1.0000 0.0070
-12.500 -1.2568 0.02065 0.01549 -0.0165 1.0000 0.0073
-12.250 -1.2389 0.01999 0.01475 -0.0152 1.0000 0.0075
-12.000 -1.2203 0.01937 0.01404 -0.0140 1.0000 0.0077
-11.750 -1.2025 0.01867 0.01327 -0.0126 1.0000 0.0081
-11.500 -1.1842 0.01803 0.01258 -0.0113 1.0000 0.0086
-11.250 -1.1656 0.01747 0.01197 -0.0099 1.0000 0.0091
-11.000 -1.1469 0.01695 0.01140 -0.0085 1.0000 0.0096
-10.750 -1.1284 0.01648 0.01087 -0.0070 1.0000 0.0101
-10.500 -1.1098 0.01603 0.01037 -0.0055 1.0000 0.0107
-10.250 -1.0915 0.01557 0.00988 -0.0039 1.0000 0.0117
-10.000 -1.0730 0.01517 0.00947 -0.0023 1.0000 0.0127
-9.750 -1.0545 0.01481 0.00908 -0.0007 1.0000 0.0136
-9.500 -1.0334 0.01444 0.00867 0.0004 0.9997 0.0146
-9.250 -1.0046 0.01409 0.00833 -0.0002 0.9986 0.0161
-9.000 -0.9754 0.01377 0.00801 -0.0009 0.9973 0.0174
-8.750 -0.9457 0.01349 0.00768 -0.0016 0.9961 0.0185
-8.500 -0.9159 0.01317 0.00733 -0.0024 0.9950 0.0194
-8.250 -0.8863 0.01283 0.00700 -0.0031 0.9938 0.0207
-8.000 -0.8577 0.01255 0.00672 -0.0036 0.9919 0.0217
-7.750 -0.8282 0.01229 0.00644 -0.0042 0.9902 0.0228
-7.500 -0.7980 0.01205 0.00617 -0.0050 0.9886 0.0238
-7.250 -0.7674 0.01180 0.00589 -0.0058 0.9872 0.0245
-7.000 -0.7363 0.01158 0.00565 -0.0068 0.9860 0.0250
-6.750 -0.7055 0.01132 0.00537 -0.0077 0.9847 0.0255
-6.500 -0.6796 0.01090 0.00491 -0.0075 0.9810 0.0269
-6.250 -0.6511 0.01059 0.00459 -0.0078 0.9781 0.0281
-6.000 -0.6218 0.01032 0.00432 -0.0083 0.9756 0.0292
-5.750 -0.5924 0.01007 0.00405 -0.0088 0.9732 0.0300
-5.500 -0.5661 0.00985 0.00381 -0.0086 0.9685 0.0307
-5.250 -0.5380 0.00964 0.00358 -0.0088 0.9647 0.0315
-5.000 -0.5093 0.00944 0.00336 -0.0090 0.9615 0.0321
-4.750 -0.4833 0.00926 0.00315 -0.0087 0.9561 0.0326
-4.500 -0.4561 0.00908 0.00296 -0.0086 0.9511 0.0330
-4.250 -0.4288 0.00889 0.00275 -0.0085 0.9466 0.0343
-4.000 -0.4026 0.00870 0.00257 -0.0082 0.9405 0.0368
-3.750 -0.3759 0.00853 0.00241 -0.0080 0.9348 0.0398
-3.500 -0.3492 0.00835 0.00226 -0.0078 0.9289 0.0457
-3.250 -0.3232 0.00813 0.00210 -0.0074 0.9220 0.0612
-3.000 -0.2968 0.00793 0.00196 -0.0072 0.9157 0.0781
-2.750 -0.2705 0.00774 0.00183 -0.0069 0.9082 0.0955
-2.500 -0.2442 0.00754 0.00170 -0.0066 0.9011 0.1195
-2.250 -0.2181 0.00732 0.00159 -0.0063 0.8929 0.1507
-2.000 -0.1924 0.00706 0.00147 -0.0060 0.8850 0.1936
-1.750 -0.1668 0.00679 0.00136 -0.0056 0.8761 0.2410
-1.500 -0.1414 0.00650 0.00125 -0.0052 0.8672 0.2970
-1.250 -0.1174 0.00609 0.00113 -0.0046 0.8577 0.3870
-1.000 -0.0928 0.00575 0.00104 -0.0040 0.8470 0.4621
-0.750 -0.0680 0.00550 0.00096 -0.0034 0.8327 0.5248
-0.500 -0.0453 0.00518 0.00089 -0.0024 0.8122 0.6136
-0.250 -0.0228 0.00496 0.00084 -0.0012 0.7828 0.6880
0.000 0.0000 0.00493 0.00083 0.0000 0.7386 0.7388
0.250 0.0230 0.00495 0.00084 0.0012 0.6912 0.7829
0.500 0.0453 0.00517 0.00089 0.0024 0.6143 0.8121
0.750 0.0681 0.00549 0.00096 0.0034 0.5272 0.8327
1.000 0.0928 0.00575 0.00104 0.0040 0.4633 0.8470
1.250 0.1174 0.00609 0.00113 0.0046 0.3868 0.8577
1.500 0.1414 0.00650 0.00125 0.0052 0.2989 0.8672
1.750 0.1668 0.00678 0.00136 0.0056 0.2427 0.8761
2.000 0.1923 0.00706 0.00147 0.0060 0.1926 0.8850
2.250 0.2181 0.00732 0.00159 0.0063 0.1503 0.8929
2.500 0.2442 0.00754 0.00170 0.0066 0.1194 0.9011
2.750 0.2704 0.00774 0.00183 0.0069 0.0952 0.9082
3.000 0.2968 0.00793 0.00196 0.0072 0.0782 0.9157
3.250 0.3232 0.00813 0.00210 0.0074 0.0612 0.9220
3.500 0.3492 0.00835 0.00225 0.0078 0.0456 0.9289
3.750 0.3758 0.00853 0.00241 0.0080 0.0398 0.9348
4.000 0.4026 0.00870 0.00257 0.0082 0.0368 0.9405
4.250 0.4288 0.00889 0.00275 0.0085 0.0342 0.9465
4.500 0.4561 0.00908 0.00296 0.0086 0.0330 0.9511
4.750 0.4833 0.00926 0.00315 0.0087 0.0326 0.9560
5.000 0.5093 0.00944 0.00336 0.0090 0.0321 0.9615
5.250 0.5380 0.00964 0.00359 0.0088 0.0315 0.9647
5.500 0.5661 0.00985 0.00381 0.0086 0.0307 0.9686
5.750 0.5923 0.01007 0.00405 0.0089 0.0300 0.9733
6.000 0.6218 0.01032 0.00432 0.0083 0.0292 0.9757
6.250 0.6512 0.01059 0.00459 0.0078 0.0281 0.9781
6.500 0.6796 0.01090 0.00491 0.0075 0.0269 0.9810
6.750 0.7056 0.01132 0.00537 0.0077 0.0255 0.9847
7.000 0.7364 0.01158 0.00565 0.0068 0.0250 0.9860
7.250 0.7675 0.01180 0.00590 0.0058 0.0245 0.9873
7.500 0.7982 0.01205 0.00617 0.0049 0.0238 0.9886
7.750 0.8284 0.01229 0.00644 0.0042 0.0228 0.9902
8.000 0.8578 0.01255 0.00672 0.0035 0.0217 0.9920
8.250 0.8864 0.01283 0.00700 0.0031 0.0207 0.9938
8.500 0.9160 0.01317 0.00733 0.0024 0.0194 0.9950
8.750 0.9459 0.01349 0.00768 0.0016 0.0185 0.9961
9.000 0.9756 0.01378 0.00801 0.0008 0.0174 0.9973
9.250 1.0048 0.01409 0.00833 0.0002 0.0161 0.9986
9.500 1.0337 0.01444 0.00867 -0.0005 0.0146 0.9997
9.750 1.0545 0.01481 0.00908 0.0007 0.0136 1.0000
10.000 1.0730 0.01517 0.00947 0.0023 0.0127 1.0000
10.250 1.0915 0.01557 0.00988 0.0039 0.0117 1.0000
10.500 1.1098 0.01603 0.01037 0.0055 0.0107 1.0000
10.750 1.1284 0.01648 0.01087 0.0070 0.0101 1.0000
11.000 1.1470 0.01695 0.01140 0.0085 0.0096 1.0000
11.250 1.1657 0.01746 0.01196 0.0099 0.0091 1.0000
11.500 1.1843 0.01803 0.01258 0.0113 0.0086 1.0000
11.750 1.2026 0.01867 0.01327 0.0126 0.0081 1.0000
12.000 1.2204 0.01937 0.01404 0.0140 0.0077 1.0000
12.250 1.2390 0.01998 0.01475 0.0152 0.0075 1.0000
12.500 1.2569 0.02065 0.01549 0.0165 0.0073 1.0000
12.750 1.2742 0.02135 0.01629 0.0178 0.0070 1.0000
13.000 1.2907 0.02211 0.01712 0.0192 0.0068 1.0000
13.250 1.3062 0.02291 0.01800 0.0207 0.0065 1.0000
13.500 1.3199 0.02376 0.01894 0.0224 0.0063 1.0000
13.750 1.3306 0.02469 0.01995 0.0246 0.0060 1.0000
14.000 1.3391 0.02576 0.02113 0.0269 0.0058 1.0000
14.250 1.3453 0.02702 0.02250 0.0293 0.0056 1.0000
14.500 1.3534 0.02814 0.02372 0.0313 0.0055 1.0000
14.750 1.3601 0.02938 0.02508 0.0332 0.0054 1.0000
15.000 1.3653 0.03078 0.02660 0.0351 0.0053 1.0000
15.250 1.3687 0.03239 0.02833 0.0368 0.0053 1.0000
15.500 1.3705 0.03421 0.03028 0.0382 0.0052 1.0000
15.750 1.3703 0.03633 0.03253 0.0394 0.0051 1.0000
16.000 1.3679 0.03880 0.03513 0.0402 0.0050 1.0000
16.250 1.3631 0.04172 0.03819 0.0404 0.0050 1.0000
16.500 1.3549 0.04529 0.04191 0.0400 0.0049 1.0000
16.750 1.3429 0.04974 0.04652 0.0386 0.0049 1.0000
17.000 1.3252 0.05558 0.05253 0.0357 0.0048 1.0000
17.250 1.2958 0.06433 0.06150 0.0302 0.0049 1.0000
17.500 1.0065 0.12838 0.12632 -0.0066 0.0059 1.0000
17.750 0.8644 0.16764 0.16586 -0.0269 0.0064 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0010-64 (naca001064-il)