NACA 4412 (naca4412-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 4412 (naca4412-il) Reynolds number: 100,000 Max Cl/Cd: 56.09 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4412-il-100000.txt Download as CSV file: xf-naca4412-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4412
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3426 0.10705 0.10189 -0.0379 1.0000 0.1297
-9.250 -0.3784 0.10671 0.10171 -0.0397 1.0000 0.1327
-9.000 -0.4173 0.10641 0.10160 -0.0391 1.0000 0.1332
-8.750 -0.3682 0.09949 0.09457 -0.0361 1.0000 0.1363
-8.500 -0.3611 0.09726 0.09235 -0.0338 1.0000 0.1402
-8.250 -0.3724 0.09561 0.09079 -0.0319 1.0000 0.1442
-8.000 -0.4032 0.09481 0.09013 -0.0296 1.0000 0.1469
-7.750 -0.4436 0.09403 0.08951 -0.0287 1.0000 0.1481
-7.500 -0.4819 0.09082 0.08639 -0.0339 1.0000 0.1493
-7.250 -0.4471 0.08830 0.08388 -0.0235 1.0000 0.1526
-7.000 -0.4480 0.08640 0.08202 -0.0209 1.0000 0.1558
-6.750 -0.4588 0.08412 0.07980 -0.0206 1.0000 0.1600
-6.500 -0.4847 0.07929 0.07495 -0.0287 1.0000 0.1662
-6.250 -0.4783 0.07718 0.07290 -0.0243 1.0000 0.1680
-6.000 -0.4744 0.07516 0.07091 -0.0219 1.0000 0.1710
-5.750 -0.4612 0.06965 0.06522 -0.0315 0.9966 0.1830
-5.500 -0.4309 0.06730 0.06289 -0.0316 0.9913 0.1898
-5.250 -0.3801 0.03672 0.02954 -0.0608 0.9884 0.1054
-5.000 -0.3390 0.03524 0.02804 -0.0644 0.9827 0.1094
-4.750 -0.2986 0.03253 0.02478 -0.0679 0.9764 0.1116
-4.500 -0.2547 0.03033 0.02199 -0.0716 0.9711 0.1152
-4.250 -0.2155 0.02874 0.02008 -0.0743 0.9639 0.1211
-4.000 -0.1732 0.02773 0.01892 -0.0774 0.9576 0.1286
-3.750 -0.1342 0.02656 0.01755 -0.0797 0.9500 0.1373
-3.500 -0.0916 0.02579 0.01667 -0.0827 0.9435 0.1516
-3.250 -0.0546 0.02511 0.01596 -0.0846 0.9347 0.1675
-3.000 -0.0135 0.02457 0.01552 -0.0873 0.9278 0.1881
-2.750 0.0233 0.02414 0.01507 -0.0891 0.9186 0.2119
-2.500 0.0621 0.02363 0.01470 -0.0912 0.9110 0.2389
-2.250 0.0998 0.02306 0.01425 -0.0931 0.9024 0.2721
-2.000 0.1378 0.02248 0.01382 -0.0950 0.8945 0.3153
-1.750 0.1759 0.02179 0.01342 -0.0968 0.8865 0.3683
-1.500 0.2137 0.02102 0.01305 -0.0985 0.8792 0.4420
-1.250 0.2473 0.02001 0.01285 -0.0990 0.8713 0.6046
-1.000 0.3011 0.01877 0.01237 -0.1014 0.8681 1.0000
-0.750 0.3304 0.01877 0.01214 -0.1016 0.8562 1.0000
-0.500 0.3765 0.01838 0.01153 -0.1044 0.8513 1.0000
-0.250 0.4028 0.01841 0.01142 -0.1039 0.8387 1.0000
0.000 0.4335 0.01835 0.01123 -0.1041 0.8283 1.0000
0.250 0.4720 0.01803 0.01077 -0.1054 0.8210 1.0000
0.500 0.4988 0.01808 0.01072 -0.1049 0.8090 1.0000
0.750 0.5348 0.01782 0.01035 -0.1058 0.8013 1.0000
1.000 0.5631 0.01782 0.01026 -0.1055 0.7900 1.0000
1.250 0.5902 0.01789 0.01027 -0.1051 0.7784 1.0000
1.500 0.6265 0.01763 0.00990 -0.1059 0.7710 1.0000
1.750 0.6506 0.01784 0.01006 -0.1050 0.7582 1.0000
2.000 0.6774 0.01798 0.01015 -0.1045 0.7469 1.0000
2.250 0.7110 0.01786 0.00993 -0.1050 0.7386 1.0000
2.500 0.7347 0.01814 0.01020 -0.1041 0.7259 1.0000
2.750 0.7611 0.01836 0.01039 -0.1036 0.7150 1.0000
3.000 0.7929 0.01834 0.01028 -0.1038 0.7060 1.0000
3.250 0.8161 0.01870 0.01065 -0.1029 0.6937 1.0000
3.500 0.8423 0.01895 0.01090 -0.1024 0.6829 1.0000
3.750 0.8728 0.01902 0.01091 -0.1024 0.6736 1.0000
4.000 0.8957 0.01941 0.01134 -0.1015 0.6614 1.0000
4.250 0.9217 0.01970 0.01163 -0.1010 0.6508 1.0000
4.500 0.9513 0.01982 0.01170 -0.1009 0.6411 1.0000
4.750 0.9739 0.02025 0.01220 -0.0999 0.6291 1.0000
5.000 0.9995 0.02057 0.01254 -0.0994 0.6185 1.0000
5.250 1.0286 0.02074 0.01268 -0.0992 0.6086 1.0000
5.500 1.0508 0.02119 0.01322 -0.0982 0.5964 1.0000
5.750 1.0755 0.02148 0.01355 -0.0974 0.5844 1.0000
6.000 1.1016 0.02159 0.01364 -0.0966 0.5709 1.0000
6.250 1.1279 0.02168 0.01370 -0.0958 0.5569 1.0000
6.500 1.1534 0.02184 0.01386 -0.0950 0.5432 1.0000
6.750 1.1757 0.02207 0.01413 -0.0937 0.5281 1.0000
7.000 1.1987 0.02216 0.01423 -0.0924 0.5114 1.0000
7.250 1.2212 0.02223 0.01428 -0.0911 0.4939 1.0000
7.500 1.2409 0.02240 0.01449 -0.0893 0.4761 1.0000
7.750 1.2594 0.02262 0.01478 -0.0875 0.4582 1.0000
8.000 1.2769 0.02285 0.01510 -0.0854 0.4393 1.0000
8.250 1.2933 0.02308 0.01539 -0.0832 0.4192 1.0000
8.500 1.3086 0.02333 0.01564 -0.0809 0.3979 1.0000
8.750 1.3197 0.02372 0.01612 -0.0779 0.3730 1.0000
9.000 1.3281 0.02421 0.01659 -0.0746 0.3445 1.0000
9.250 1.3316 0.02495 0.01728 -0.0707 0.3104 1.0000
9.500 1.3276 0.02605 0.01816 -0.0657 0.2733 1.0000
9.750 1.3204 0.02765 0.01952 -0.0608 0.2346 1.0000
10.000 1.3127 0.02965 0.02123 -0.0564 0.2023 1.0000
10.250 1.3077 0.03176 0.02308 -0.0527 0.1788 1.0000
10.500 1.3074 0.03378 0.02497 -0.0497 0.1606 1.0000
10.750 1.3110 0.03571 0.02678 -0.0472 0.1474 1.0000
11.000 1.3189 0.03755 0.02847 -0.0451 0.1369 1.0000
11.250 1.3289 0.03922 0.03015 -0.0434 0.1279 1.0000
11.500 1.3439 0.04092 0.03184 -0.0420 0.1203 1.0000
11.750 1.3595 0.04250 0.03339 -0.0408 0.1136 1.0000
12.000 1.3787 0.04430 0.03522 -0.0399 0.1076 1.0000
12.250 1.3912 0.04604 0.03710 -0.0386 0.1025 1.0000
12.500 1.4202 0.04801 0.03893 -0.0387 0.0966 1.0000
12.750 1.4239 0.05002 0.04125 -0.0367 0.0932 1.0000
13.000 1.4319 0.05205 0.04343 -0.0351 0.0895 1.0000
13.250 1.4604 0.05447 0.04574 -0.0355 0.0845 1.0000
13.500 1.4540 0.05696 0.04860 -0.0329 0.0825 1.0000
13.750 1.4507 0.05963 0.05156 -0.0309 0.0802 1.0000
14.000 1.4512 0.06218 0.05428 -0.0294 0.0775 1.0000
14.250 1.4783 0.06519 0.05713 -0.0297 0.0734 1.0000
14.500 1.4597 0.06850 0.06082 -0.0274 0.0727 1.0000
14.750 1.4404 0.07234 0.06501 -0.0257 0.0720 1.0000
15.000 1.4201 0.07667 0.06967 -0.0247 0.0712 1.0000
15.250 1.3983 0.08150 0.07481 -0.0243 0.0706 1.0000
15.500 1.3742 0.08690 0.08051 -0.0247 0.0701 1.0000
15.750 1.3474 0.09302 0.08692 -0.0259 0.0699 1.0000
16.000 1.3171 0.10006 0.09424 -0.0282 0.0701 1.0000
16.250 1.2836 0.10833 0.10277 -0.0317 0.0706 1.0000
16.500 1.2473 0.11795 0.11263 -0.0367 0.0714 1.0000
16.750 1.2101 0.12886 0.12372 -0.0430 0.0723 1.0000
17.000 1.1753 0.14068 0.13565 -0.0500 0.0732 1.0000
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