NACA 63-412 AIRFOIL (n63412-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-412 AIRFOIL (n63412-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.66 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63412-il-1000000-n5.txt Download as CSV file: xf-n63412-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.9681 0.07832 0.07592 -0.0461 1.0000 0.0061
-16.250 -1.0143 0.06526 0.06263 -0.0546 1.0000 0.0060
-16.000 -1.0409 0.05685 0.05404 -0.0604 1.0000 0.0059
-15.750 -1.0622 0.05000 0.04703 -0.0650 1.0000 0.0060
-15.500 -1.0788 0.04436 0.04123 -0.0686 1.0000 0.0061
-15.250 -1.0869 0.04026 0.03700 -0.0709 1.0000 0.0061
-15.000 -1.0925 0.03675 0.03336 -0.0726 1.0000 0.0062
-14.750 -1.0945 0.03389 0.03039 -0.0736 1.0000 0.0062
-14.500 -1.0920 0.03170 0.02811 -0.0741 1.0000 0.0063
-14.250 -1.0919 0.02948 0.02578 -0.0741 1.0000 0.0064
-14.000 -1.0864 0.02795 0.02416 -0.0737 1.0000 0.0066
-13.750 -1.0846 0.02637 0.02249 -0.0727 1.0000 0.0066
-13.500 -1.0834 0.02518 0.02122 -0.0707 1.0000 0.0067
-13.250 -1.0741 0.02419 0.02015 -0.0694 1.0000 0.0069
-13.000 -1.0625 0.02321 0.01909 -0.0682 1.0000 0.0070
-12.750 -1.0492 0.02232 0.01811 -0.0670 1.0000 0.0072
-12.500 -1.0339 0.02154 0.01726 -0.0659 1.0000 0.0074
-12.250 -1.0185 0.02073 0.01637 -0.0647 1.0000 0.0075
-12.000 -1.0004 0.02005 0.01561 -0.0639 0.9998 0.0078
-11.500 -0.9441 0.01844 0.01381 -0.0662 0.9889 0.0082
-11.250 -0.9140 0.01757 0.01287 -0.0678 0.9836 0.0085
-11.000 -0.8823 0.01693 0.01219 -0.0694 0.9772 0.0089
-10.750 -0.8496 0.01630 0.01150 -0.0712 0.9695 0.0092
-10.500 -0.8160 0.01574 0.01086 -0.0731 0.9607 0.0096
-10.250 -0.7840 0.01518 0.01022 -0.0746 0.9485 0.0100
-9.750 -0.7302 0.01431 0.00914 -0.0752 0.9190 0.0106
-9.500 -0.7061 0.01382 0.00856 -0.0749 0.9060 0.0110
-9.250 -0.6815 0.01341 0.00809 -0.0746 0.8944 0.0115
-9.000 -0.6564 0.01311 0.00772 -0.0744 0.8832 0.0120
-8.500 -0.6057 0.01251 0.00696 -0.0739 0.8590 0.0130
-8.250 -0.5800 0.01220 0.00657 -0.0737 0.8473 0.0135
-8.000 -0.5541 0.01192 0.00619 -0.0736 0.8375 0.0138
-7.750 -0.5282 0.01153 0.00574 -0.0735 0.8284 0.0143
-7.500 -0.5018 0.01122 0.00539 -0.0735 0.8205 0.0151
-7.250 -0.4750 0.01097 0.00510 -0.0734 0.8123 0.0158
-7.000 -0.4480 0.01073 0.00481 -0.0734 0.8047 0.0165
-6.750 -0.4209 0.01050 0.00451 -0.0735 0.7966 0.0171
-6.500 -0.3936 0.01028 0.00423 -0.0735 0.7893 0.0176
-6.250 -0.3664 0.01000 0.00390 -0.0735 0.7820 0.0186
-6.000 -0.3389 0.00977 0.00365 -0.0736 0.7752 0.0199
-5.750 -0.3112 0.00957 0.00341 -0.0737 0.7677 0.0209
-5.500 -0.2835 0.00940 0.00319 -0.0738 0.7607 0.0219
-5.250 -0.2555 0.00923 0.00298 -0.0739 0.7536 0.0227
-5.000 -0.2278 0.00903 0.00275 -0.0740 0.7471 0.0251
-4.750 -0.1996 0.00886 0.00257 -0.0741 0.7402 0.0272
-4.500 -0.1715 0.00874 0.00239 -0.0742 0.7330 0.0288
-4.250 -0.1433 0.00856 0.00222 -0.0744 0.7263 0.0324
-4.000 -0.1151 0.00844 0.00207 -0.0746 0.7191 0.0360
-3.750 -0.0868 0.00828 0.00192 -0.0747 0.7125 0.0429
-3.500 -0.0585 0.00813 0.00178 -0.0749 0.7051 0.0536
-3.000 -0.0019 0.00773 0.00151 -0.0754 0.6912 0.1021
-2.750 0.0262 0.00746 0.00138 -0.0756 0.6844 0.1495
-2.500 0.0545 0.00712 0.00124 -0.0760 0.6773 0.2160
-2.250 0.0826 0.00673 0.00110 -0.0764 0.6703 0.3012
-2.000 0.1111 0.00641 0.00101 -0.0768 0.6635 0.3768
-1.750 0.1395 0.00623 0.00096 -0.0771 0.6563 0.4309
-1.500 0.1681 0.00605 0.00094 -0.0774 0.6495 0.4880
-1.250 0.1967 0.00599 0.00093 -0.0776 0.6423 0.5168
-1.000 0.2254 0.00594 0.00093 -0.0778 0.6355 0.5432
-0.750 0.2541 0.00592 0.00094 -0.0780 0.6282 0.5616
-0.500 0.2828 0.00594 0.00094 -0.0781 0.6216 0.5722
-0.250 0.3115 0.00595 0.00095 -0.0783 0.6140 0.5829
0.000 0.3401 0.00597 0.00096 -0.0785 0.6070 0.5917
0.250 0.3688 0.00599 0.00098 -0.0786 0.5991 0.6000
0.500 0.3973 0.00602 0.00101 -0.0788 0.5916 0.6077
0.750 0.4259 0.00605 0.00104 -0.0789 0.5830 0.6156
1.000 0.4544 0.00609 0.00108 -0.0790 0.5749 0.6236
1.250 0.4829 0.00614 0.00112 -0.0792 0.5660 0.6320
1.500 0.5113 0.00618 0.00118 -0.0793 0.5572 0.6407
1.750 0.5395 0.00625 0.00124 -0.0794 0.5466 0.6500
2.250 0.5954 0.00643 0.00139 -0.0795 0.5199 0.6683
2.500 0.6232 0.00655 0.00147 -0.0795 0.5047 0.6774
2.750 0.6508 0.00668 0.00157 -0.0795 0.4863 0.6855
3.000 0.6778 0.00687 0.00168 -0.0794 0.4592 0.6934
3.250 0.7032 0.00722 0.00185 -0.0791 0.4094 0.7008
3.500 0.7280 0.00765 0.00206 -0.0787 0.3560 0.7081
3.750 0.7529 0.00807 0.00231 -0.0783 0.3092 0.7149
4.000 0.7768 0.00861 0.00261 -0.0779 0.2532 0.7222
4.250 0.8001 0.00920 0.00295 -0.0773 0.1951 0.7288
4.500 0.8233 0.00979 0.00331 -0.0768 0.1426 0.7362
4.750 0.8470 0.01032 0.00366 -0.0763 0.1009 0.7433
5.000 0.8715 0.01074 0.00398 -0.0758 0.0740 0.7509
5.250 0.8962 0.01112 0.00428 -0.0755 0.0549 0.7583
5.500 0.9212 0.01146 0.00459 -0.0751 0.0424 0.7665
5.750 0.9463 0.01177 0.00488 -0.0748 0.0341 0.7743
6.000 0.9715 0.01206 0.00518 -0.0744 0.0295 0.7830
6.250 0.9966 0.01234 0.00547 -0.0741 0.0261 0.7914
6.500 1.0216 0.01262 0.00578 -0.0737 0.0234 0.8007
6.750 1.0461 0.01294 0.00612 -0.0733 0.0208 0.8100
7.000 1.0707 0.01322 0.00644 -0.0728 0.0190 0.8197
7.250 1.0945 0.01356 0.00680 -0.0723 0.0169 0.8306
7.500 1.1181 0.01388 0.00718 -0.0717 0.0155 0.8416
7.750 1.1414 0.01421 0.00756 -0.0711 0.0144 0.8533
8.000 1.1640 0.01458 0.00796 -0.0703 0.0134 0.8659
8.250 1.1854 0.01500 0.00844 -0.0694 0.0125 0.8797
8.500 1.2068 0.01535 0.00886 -0.0684 0.0121 0.8951
8.750 1.2267 0.01569 0.00930 -0.0671 0.0117 0.9152
9.000 1.2460 0.01599 0.00972 -0.0657 0.0114 1.0000
9.250 1.2672 0.01647 0.01022 -0.0649 0.0110 1.0000
9.500 1.2877 0.01696 0.01074 -0.0640 0.0106 1.0000
9.750 1.3072 0.01750 0.01130 -0.0629 0.0102 1.0000
10.000 1.3250 0.01811 0.01195 -0.0616 0.0099 1.0000
10.250 1.3394 0.01879 0.01268 -0.0597 0.0096 1.0000
10.500 1.3520 0.01947 0.01341 -0.0575 0.0094 1.0000
10.750 1.3654 0.02011 0.01410 -0.0555 0.0093 1.0000
11.000 1.3783 0.02079 0.01484 -0.0536 0.0092 1.0000
11.250 1.3903 0.02156 0.01568 -0.0517 0.0091 1.0000
11.500 1.4018 0.02239 0.01658 -0.0498 0.0090 1.0000
11.750 1.4128 0.02329 0.01755 -0.0481 0.0089 1.0000
12.000 1.4237 0.02426 0.01858 -0.0464 0.0087 1.0000
12.250 1.4339 0.02530 0.01969 -0.0449 0.0086 1.0000
12.500 1.4446 0.02636 0.02080 -0.0435 0.0084 1.0000
12.750 1.4534 0.02761 0.02212 -0.0420 0.0083 1.0000
13.000 1.4622 0.02891 0.02350 -0.0407 0.0082 1.0000
13.250 1.4705 0.03030 0.02497 -0.0395 0.0081 1.0000
13.500 1.4780 0.03181 0.02655 -0.0384 0.0079 1.0000
13.750 1.4848 0.03344 0.02826 -0.0374 0.0078 1.0000
14.000 1.4907 0.03521 0.03010 -0.0365 0.0077 1.0000
14.250 1.4960 0.03710 0.03207 -0.0357 0.0076 1.0000
14.500 1.5001 0.03918 0.03423 -0.0350 0.0075 1.0000
14.750 1.5032 0.04142 0.03655 -0.0345 0.0074 1.0000
15.000 1.5033 0.04407 0.03930 -0.0341 0.0073 1.0000
15.250 1.5014 0.04705 0.04238 -0.0338 0.0072 1.0000
15.500 1.4958 0.05058 0.04603 -0.0339 0.0070 1.0000
15.750 1.4985 0.05326 0.04881 -0.0341 0.0070 1.0000
16.000 1.5000 0.05619 0.05185 -0.0344 0.0069 1.0000
16.250 1.4988 0.05957 0.05534 -0.0350 0.0069 1.0000
16.500 1.4969 0.06318 0.05906 -0.0359 0.0068 1.0000
16.750 1.4949 0.06694 0.06293 -0.0369 0.0068 1.0000
17.000 1.4909 0.07110 0.06721 -0.0382 0.0067 1.0000
17.250 1.4857 0.07560 0.07184 -0.0398 0.0067 1.0000
17.500 1.4802 0.08031 0.07666 -0.0416 0.0066 1.0000
17.750 1.4734 0.08538 0.08186 -0.0437 0.0066 1.0000
18.000 1.4642 0.09101 0.08762 -0.0462 0.0065 1.0000
18.250 1.4542 0.09698 0.09371 -0.0491 0.0065 1.0000
18.500 1.4433 0.10330 0.10017 -0.0523 0.0065 1.0000
18.750 1.4301 0.11024 0.10725 -0.0559 0.0064 1.0000
19.000 1.4164 0.11746 0.11460 -0.0599 0.0064 1.0000
19.250 1.4014 0.12518 0.12246 -0.0644 0.0064 1.0000
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