NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(1)-412 (naca651412-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.92 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca651412-il-1000000-n5.txt Download as CSV file: xf-naca651412-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-412
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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9366 0.05435 0.05211 -0.0728 1.0000 0.0059
-15.000 -0.9672 0.04669 0.04424 -0.0777 1.0000 0.0059
-14.750 -0.9875 0.04145 0.03880 -0.0800 1.0000 0.0059
-14.500 -1.0004 0.03761 0.03479 -0.0809 1.0000 0.0059
-14.250 -1.0082 0.03464 0.03165 -0.0809 1.0000 0.0060
-14.000 -1.0107 0.03244 0.02932 -0.0802 1.0000 0.0060
-13.750 -1.0174 0.03016 0.02689 -0.0788 1.0000 0.0060
-13.500 -1.0240 0.02829 0.02489 -0.0764 1.0000 0.0062
-13.250 -1.0300 0.02704 0.02354 -0.0729 1.0000 0.0063
-13.000 -1.0208 0.02589 0.02230 -0.0716 0.9986 0.0064
-12.750 -0.9994 0.02477 0.02108 -0.0723 0.9906 0.0066
-12.500 -0.9733 0.02373 0.01995 -0.0738 0.9858 0.0068
-12.250 -0.9464 0.02272 0.01883 -0.0753 0.9801 0.0070
-11.750 -0.8875 0.02091 0.01680 -0.0788 0.9683 0.0076
-11.500 -0.8583 0.01993 0.01569 -0.0804 0.9608 0.0078
-11.250 -0.8310 0.01905 0.01467 -0.0815 0.9510 0.0081
-11.000 -0.8068 0.01832 0.01381 -0.0817 0.9394 0.0083
-10.750 -0.7855 0.01752 0.01287 -0.0814 0.9280 0.0085
-10.500 -0.7641 0.01687 0.01210 -0.0808 0.9174 0.0088
-10.250 -0.7412 0.01648 0.01163 -0.0804 0.9075 0.0091
-10.000 -0.7181 0.01608 0.01116 -0.0800 0.8987 0.0093
-9.500 -0.6715 0.01527 0.01019 -0.0792 0.8815 0.0099
-9.250 -0.6483 0.01480 0.00962 -0.0788 0.8735 0.0102
-9.000 -0.6243 0.01440 0.00912 -0.0785 0.8653 0.0106
-8.750 -0.5999 0.01406 0.00869 -0.0782 0.8578 0.0110
-8.500 -0.5750 0.01373 0.00828 -0.0779 0.8500 0.0112
-8.250 -0.5521 0.01310 0.00756 -0.0775 0.8429 0.0117
-8.000 -0.5271 0.01277 0.00718 -0.0773 0.8355 0.0121
-7.750 -0.5019 0.01247 0.00681 -0.0771 0.8287 0.0124
-7.500 -0.4762 0.01217 0.00647 -0.0770 0.8216 0.0129
-7.000 -0.4247 0.01158 0.00576 -0.0768 0.8090 0.0138
-6.750 -0.3986 0.01132 0.00543 -0.0767 0.8025 0.0143
-6.500 -0.3724 0.01106 0.00510 -0.0766 0.7965 0.0146
-6.250 -0.3466 0.01068 0.00466 -0.0765 0.7899 0.0150
-6.000 -0.3209 0.01031 0.00423 -0.0764 0.7839 0.0157
-5.750 -0.2939 0.01007 0.00397 -0.0764 0.7782 0.0163
-5.500 -0.2670 0.00987 0.00374 -0.0765 0.7724 0.0170
-5.250 -0.2400 0.00965 0.00348 -0.0765 0.7671 0.0176
-5.000 -0.2127 0.00944 0.00322 -0.0766 0.7611 0.0182
-4.750 -0.1856 0.00926 0.00299 -0.0767 0.7554 0.0188
-4.500 -0.1580 0.00909 0.00278 -0.0768 0.7499 0.0192
-4.250 -0.1306 0.00884 0.00250 -0.0769 0.7444 0.0205
-4.000 -0.1031 0.00868 0.00232 -0.0770 0.7395 0.0220
-3.750 -0.0751 0.00854 0.00216 -0.0772 0.7346 0.0234
-3.500 -0.0472 0.00842 0.00201 -0.0774 0.7293 0.0247
-3.250 -0.0194 0.00830 0.00186 -0.0775 0.7243 0.0263
-3.000 0.0087 0.00815 0.00172 -0.0777 0.7194 0.0298
-2.750 0.0368 0.00805 0.00161 -0.0779 0.7146 0.0328
-2.500 0.0648 0.00794 0.00149 -0.0781 0.7100 0.0406
-2.250 0.0929 0.00773 0.00139 -0.0784 0.7055 0.0701
-2.000 0.1207 0.00741 0.00127 -0.0787 0.7006 0.1374
-1.750 0.1482 0.00697 0.00113 -0.0791 0.6961 0.2435
-1.500 0.1752 0.00605 0.00094 -0.0799 0.6920 0.4697
-1.000 0.2316 0.00564 0.00096 -0.0805 0.6828 0.6215
-0.750 0.2600 0.00562 0.00097 -0.0807 0.6787 0.6413
-0.500 0.2888 0.00561 0.00098 -0.0810 0.6744 0.6543
-0.250 0.3175 0.00562 0.00100 -0.0812 0.6699 0.6613
0.000 0.3460 0.00566 0.00100 -0.0815 0.6657 0.6660
0.250 0.3748 0.00567 0.00102 -0.0817 0.6617 0.6703
0.500 0.4035 0.00568 0.00104 -0.0820 0.6575 0.6749
0.750 0.4321 0.00571 0.00107 -0.0822 0.6532 0.6798
1.000 0.4606 0.00576 0.00111 -0.0825 0.6492 0.6843
1.250 0.4893 0.00577 0.00115 -0.0827 0.6441 0.6889
1.500 0.5173 0.00582 0.00119 -0.0828 0.6362 0.6940
1.750 0.5455 0.00588 0.00124 -0.0830 0.6256 0.6988
2.000 0.5729 0.00596 0.00129 -0.0830 0.6094 0.7034
2.250 0.6002 0.00605 0.00136 -0.0830 0.5932 0.7086
2.500 0.6267 0.00621 0.00143 -0.0828 0.5649 0.7138
2.750 0.6515 0.00649 0.00155 -0.0824 0.5191 0.7187
3.000 0.6706 0.00727 0.00186 -0.0810 0.4097 0.7240
3.250 0.6890 0.00818 0.00228 -0.0797 0.2983 0.7295
3.500 0.7082 0.00900 0.00270 -0.0785 0.2020 0.7350
3.750 0.7280 0.00976 0.00310 -0.0774 0.1192 0.7411
4.000 0.7502 0.01030 0.00344 -0.0767 0.0701 0.7466
4.250 0.7734 0.01072 0.00374 -0.0760 0.0401 0.7524
4.500 0.7984 0.01099 0.00398 -0.0757 0.0312 0.7585
4.750 0.8234 0.01125 0.00423 -0.0754 0.0262 0.7646
5.000 0.8488 0.01146 0.00448 -0.0751 0.0242 0.7715
5.250 0.8736 0.01171 0.00474 -0.0747 0.0215 0.7779
5.500 0.8980 0.01198 0.00503 -0.0743 0.0192 0.7848
6.000 0.9468 0.01250 0.00561 -0.0734 0.0163 0.7985
6.250 0.9701 0.01284 0.00596 -0.0728 0.0147 0.8063
6.500 0.9935 0.01312 0.00629 -0.0722 0.0140 0.8140
7.000 1.0391 0.01375 0.00702 -0.0708 0.0127 0.8301
7.250 1.0610 0.01411 0.00741 -0.0700 0.0122 0.8381
7.500 1.0820 0.01449 0.00784 -0.0690 0.0117 0.8473
7.750 1.1014 0.01496 0.00837 -0.0677 0.0111 0.8569
8.000 1.1207 0.01541 0.00889 -0.0664 0.0108 0.8675
8.250 1.1399 0.01579 0.00935 -0.0651 0.0106 0.8789
8.500 1.1565 0.01620 0.00984 -0.0633 0.0104 0.8916
8.750 1.1709 0.01663 0.01036 -0.0610 0.0102 0.9072
9.000 1.1842 0.01709 0.01089 -0.0586 0.0101 0.9256
9.250 1.1949 0.01752 0.01145 -0.0557 0.0099 0.9546
9.500 1.2118 0.01808 0.01208 -0.0544 0.0097 1.0000
9.750 1.2272 0.01872 0.01276 -0.0528 0.0096 1.0000
10.000 1.2421 0.01940 0.01349 -0.0512 0.0094 1.0000
10.250 1.2568 0.02011 0.01426 -0.0496 0.0093 1.0000
10.500 1.2711 0.02086 0.01506 -0.0481 0.0091 1.0000
10.750 1.2850 0.02165 0.01591 -0.0466 0.0090 1.0000
11.000 1.2993 0.02243 0.01673 -0.0453 0.0088 1.0000
11.250 1.3120 0.02335 0.01771 -0.0437 0.0087 1.0000
11.500 1.3246 0.02430 0.01870 -0.0423 0.0084 1.0000
11.750 1.3346 0.02547 0.01995 -0.0407 0.0083 1.0000
12.000 1.3424 0.02688 0.02145 -0.0389 0.0081 1.0000
12.250 1.3497 0.02838 0.02304 -0.0373 0.0080 1.0000
12.500 1.3604 0.02960 0.02435 -0.0360 0.0080 1.0000
12.750 1.3712 0.03083 0.02567 -0.0348 0.0079 1.0000
13.000 1.3815 0.03212 0.02705 -0.0337 0.0078 1.0000
13.250 1.3913 0.03347 0.02849 -0.0327 0.0077 1.0000
13.500 1.4008 0.03489 0.03000 -0.0317 0.0076 1.0000
13.750 1.4086 0.03648 0.03169 -0.0307 0.0075 1.0000
14.000 1.4149 0.03829 0.03360 -0.0297 0.0074 1.0000
14.250 1.4224 0.03998 0.03538 -0.0289 0.0072 1.0000
14.500 1.4282 0.04188 0.03739 -0.0282 0.0071 1.0000
14.750 1.4322 0.04402 0.03963 -0.0275 0.0070 1.0000
15.000 1.4360 0.04623 0.04196 -0.0270 0.0069 1.0000
15.250 1.4384 0.04868 0.04453 -0.0266 0.0069 1.0000
15.500 1.4414 0.05113 0.04707 -0.0263 0.0067 1.0000
15.750 1.4430 0.05382 0.04987 -0.0263 0.0067 1.0000
16.000 1.4427 0.05685 0.05301 -0.0264 0.0066 1.0000
16.250 1.4431 0.05989 0.05616 -0.0267 0.0065 1.0000
16.500 1.4418 0.06326 0.05964 -0.0272 0.0064 1.0000
16.750 1.4385 0.06705 0.06355 -0.0280 0.0064 1.0000
17.000 1.4347 0.07106 0.06768 -0.0291 0.0063 1.0000
17.250 1.4319 0.07507 0.07179 -0.0304 0.0062 1.0000
17.500 1.4257 0.07976 0.07660 -0.0321 0.0062 1.0000
17.750 1.4202 0.08454 0.08148 -0.0341 0.0061 1.0000
18.000 1.4080 0.09069 0.08778 -0.0368 0.0061 1.0000
18.250 1.3960 0.09712 0.09433 -0.0400 0.0060 1.0000
18.500 1.3792 0.10474 0.10211 -0.0440 0.0060 1.0000
18.750 1.3600 0.11326 0.11080 -0.0488 0.0060 1.0000
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Polar data table (+)
Polar graphs
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