NACA 63-412 AIRFOIL (n63412-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63-412 AIRFOIL (n63412-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.69 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n63412-il-1000000.txt Download as CSV file: xf-n63412-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-412 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8332 0.05739 0.05518 -0.0594 1.0000 0.0096
-13.500 -0.8907 0.04486 0.04227 -0.0685 1.0000 0.0093
-13.250 -0.8936 0.04150 0.03881 -0.0705 1.0000 0.0094
-13.000 -0.8927 0.03894 0.03617 -0.0719 1.0000 0.0096
-12.750 -0.8963 0.03612 0.03323 -0.0729 1.0000 0.0097
-12.500 -0.9050 0.03317 0.03012 -0.0730 1.0000 0.0098
-12.250 -0.9157 0.03072 0.02751 -0.0716 1.0000 0.0098
-12.000 -0.9173 0.02939 0.02608 -0.0696 1.0000 0.0100
-11.750 -0.9115 0.02803 0.02460 -0.0681 1.0000 0.0102
-11.500 -0.9026 0.02683 0.02329 -0.0666 1.0000 0.0104
-11.250 -0.8924 0.02570 0.02204 -0.0651 1.0000 0.0107
-11.000 -0.8822 0.02458 0.02079 -0.0633 1.0000 0.0109
-10.750 -0.8725 0.02361 0.01970 -0.0612 1.0000 0.0111
-10.500 -0.8409 0.02256 0.01850 -0.0633 0.9978 0.0113
-10.250 -0.8160 0.01952 0.01514 -0.0655 0.9936 0.0118
-10.000 -0.7856 0.01860 0.01416 -0.0671 0.9893 0.0122
-9.750 -0.7529 0.01790 0.01341 -0.0689 0.9857 0.0126
-9.500 -0.7189 0.01725 0.01268 -0.0709 0.9828 0.0131
-9.250 -0.6880 0.01646 0.01180 -0.0723 0.9762 0.0136
-9.000 -0.6536 0.01579 0.01105 -0.0742 0.9712 0.0142
-8.750 -0.6209 0.01530 0.01048 -0.0756 0.9620 0.0146
-8.500 -0.5925 0.01400 0.00903 -0.0767 0.9498 0.0154
-8.250 -0.5647 0.01353 0.00852 -0.0771 0.9361 0.0161
-8.000 -0.5387 0.01316 0.00807 -0.0770 0.9231 0.0167
-7.750 -0.5134 0.01278 0.00761 -0.0767 0.9110 0.0174
-7.500 -0.4880 0.01241 0.00715 -0.0764 0.8997 0.0181
-7.250 -0.4620 0.01211 0.00677 -0.0762 0.8898 0.0186
-6.750 -0.4122 0.01098 0.00550 -0.0757 0.8701 0.0206
-6.500 -0.3856 0.01072 0.00519 -0.0756 0.8613 0.0216
-6.250 -0.3589 0.01045 0.00485 -0.0755 0.8523 0.0227
-6.000 -0.3317 0.01022 0.00456 -0.0755 0.8442 0.0235
-5.750 -0.3054 0.00975 0.00401 -0.0754 0.8357 0.0249
-5.500 -0.2782 0.00945 0.00368 -0.0754 0.8275 0.0268
-5.250 -0.2507 0.00926 0.00344 -0.0754 0.8196 0.0286
-5.000 -0.2228 0.00909 0.00322 -0.0755 0.8121 0.0299
-4.750 -0.1954 0.00874 0.00282 -0.0755 0.8044 0.0336
-4.500 -0.1674 0.00856 0.00262 -0.0757 0.7969 0.0369
-4.250 -0.1395 0.00834 0.00237 -0.0757 0.7894 0.0427
-4.000 -0.1114 0.00813 0.00217 -0.0759 0.7822 0.0521
-3.750 -0.0835 0.00784 0.00196 -0.0760 0.7748 0.0781
-3.500 -0.0557 0.00742 0.00176 -0.0764 0.7676 0.1409
-3.250 -0.0282 0.00684 0.00153 -0.0768 0.7602 0.2426
-3.000 -0.0006 0.00626 0.00133 -0.0773 0.7532 0.3606
-2.750 0.0276 0.00596 0.00124 -0.0776 0.7458 0.4381
-2.500 0.0561 0.00582 0.00119 -0.0778 0.7389 0.4795
-2.250 0.0847 0.00574 0.00115 -0.0780 0.7315 0.5088
-2.000 0.1133 0.00570 0.00113 -0.0781 0.7247 0.5309
-1.750 0.1421 0.00567 0.00111 -0.0783 0.7173 0.5509
-1.500 0.1705 0.00564 0.00111 -0.0784 0.7103 0.5777
-1.250 0.1993 0.00561 0.00110 -0.0785 0.7030 0.5923
-1.000 0.2277 0.00562 0.00110 -0.0786 0.6959 0.6088
-0.750 0.2566 0.00559 0.00110 -0.0788 0.6886 0.6224
-0.250 0.3139 0.00562 0.00111 -0.0791 0.6741 0.6435
0.000 0.3423 0.00565 0.00114 -0.0792 0.6666 0.6536
0.250 0.3711 0.00566 0.00116 -0.0793 0.6590 0.6631
0.750 0.4282 0.00572 0.00122 -0.0796 0.6433 0.6813
1.000 0.4566 0.00579 0.00126 -0.0797 0.6353 0.6904
1.250 0.4852 0.00581 0.00130 -0.0798 0.6269 0.6987
1.500 0.5135 0.00587 0.00135 -0.0799 0.6186 0.7070
1.750 0.5419 0.00591 0.00140 -0.0800 0.6091 0.7152
2.000 0.5702 0.00596 0.00146 -0.0800 0.5987 0.7231
2.250 0.5981 0.00603 0.00152 -0.0800 0.5877 0.7312
2.750 0.6539 0.00619 0.00166 -0.0801 0.5616 0.7469
3.000 0.6815 0.00629 0.00174 -0.0800 0.5465 0.7545
3.250 0.7088 0.00642 0.00184 -0.0799 0.5253 0.7626
3.500 0.7361 0.00655 0.00195 -0.0798 0.5069 0.7701
3.750 0.7633 0.00669 0.00206 -0.0798 0.4896 0.7781
4.000 0.7902 0.00685 0.00220 -0.0796 0.4696 0.7859
4.250 0.8168 0.00706 0.00234 -0.0795 0.4423 0.7942
4.500 0.8410 0.00747 0.00256 -0.0789 0.3899 0.8022
4.750 0.8630 0.00815 0.00292 -0.0782 0.3143 0.8112
5.000 0.8838 0.00893 0.00336 -0.0772 0.2368 0.8199
5.250 0.9050 0.00968 0.00380 -0.0764 0.1712 0.8293
5.500 0.9263 0.01037 0.00425 -0.0755 0.1177 0.8394
5.750 0.9481 0.01098 0.00469 -0.0746 0.0780 0.8496
6.000 0.9706 0.01149 0.00509 -0.0739 0.0528 0.8605
6.250 0.9939 0.01191 0.00546 -0.0732 0.0405 0.8722
6.500 1.0171 0.01226 0.00583 -0.0725 0.0339 0.8846
6.750 1.0390 0.01267 0.00626 -0.0715 0.0284 0.8985
7.000 1.0615 0.01293 0.00659 -0.0706 0.0259 0.9155
7.250 1.0790 0.01325 0.00698 -0.0686 0.0229 0.9499
7.500 1.1042 0.01365 0.00743 -0.0684 0.0209 1.0000
7.750 1.1284 0.01404 0.00783 -0.0680 0.0193 1.0000
8.000 1.1502 0.01462 0.00842 -0.0673 0.0177 1.0000
8.250 1.1715 0.01521 0.00906 -0.0664 0.0168 1.0000
8.500 1.1938 0.01567 0.00955 -0.0657 0.0162 1.0000
8.750 1.2153 0.01617 0.01008 -0.0649 0.0155 1.0000
9.000 1.2358 0.01670 0.01065 -0.0639 0.0149 1.0000
9.250 1.2552 0.01729 0.01126 -0.0628 0.0144 1.0000
9.500 1.2715 0.01805 0.01206 -0.0613 0.0138 1.0000
9.750 1.2800 0.01916 0.01325 -0.0585 0.0133 1.0000
10.000 1.2902 0.01999 0.01416 -0.0559 0.0131 1.0000
10.250 1.3046 0.02059 0.01481 -0.0541 0.0129 1.0000
10.500 1.3177 0.02129 0.01557 -0.0522 0.0126 1.0000
10.750 1.3297 0.02208 0.01642 -0.0503 0.0123 1.0000
11.000 1.3399 0.02304 0.01744 -0.0482 0.0121 1.0000
11.250 1.3506 0.02400 0.01847 -0.0465 0.0118 1.0000
11.500 1.3601 0.02510 0.01964 -0.0447 0.0116 1.0000
11.750 1.3701 0.02621 0.02081 -0.0431 0.0113 1.0000
12.000 1.3791 0.02744 0.02210 -0.0416 0.0111 1.0000
12.250 1.3879 0.02873 0.02345 -0.0402 0.0109 1.0000
12.500 1.3943 0.03030 0.02509 -0.0387 0.0107 1.0000
12.750 1.3995 0.03203 0.02690 -0.0373 0.0106 1.0000
13.000 1.4015 0.03419 0.02915 -0.0359 0.0104 1.0000
13.250 1.4009 0.03675 0.03182 -0.0345 0.0102 1.0000
13.500 1.3976 0.03980 0.03505 -0.0331 0.0100 1.0000
13.750 1.4056 0.04144 0.03677 -0.0326 0.0099 1.0000
14.000 1.4108 0.04349 0.03893 -0.0322 0.0098 1.0000
14.250 1.4148 0.04575 0.04129 -0.0318 0.0097 1.0000
14.500 1.4171 0.04827 0.04393 -0.0315 0.0095 1.0000
14.750 1.4179 0.05104 0.04682 -0.0314 0.0094 1.0000
15.000 1.4178 0.05405 0.04995 -0.0315 0.0093 1.0000
15.250 1.4164 0.05729 0.05331 -0.0319 0.0092 1.0000
15.500 1.4137 0.06087 0.05702 -0.0324 0.0091 1.0000
15.750 1.4106 0.06465 0.06092 -0.0333 0.0090 1.0000
16.000 1.4054 0.06887 0.06527 -0.0344 0.0089 1.0000
16.250 1.4001 0.07327 0.06980 -0.0359 0.0088 1.0000
16.500 1.3931 0.07814 0.07481 -0.0378 0.0088 1.0000
16.750 1.3841 0.08353 0.08035 -0.0400 0.0087 1.0000
17.000 1.3751 0.08913 0.08608 -0.0426 0.0086 1.0000
17.250 1.3638 0.09538 0.09247 -0.0456 0.0086 1.0000
17.500 1.3504 0.10228 0.09952 -0.0492 0.0085 1.0000
17.750 1.3370 0.10942 0.10681 -0.0532 0.0085 1.0000
18.000 1.3192 0.11779 0.11534 -0.0580 0.0085 1.0000
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Polar data table (+)
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