NACA 1412 (naca1412-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1412 (naca1412-il) Reynolds number: 100,000 Max Cl/Cd: 43.01 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1412-il-100000-n5.txt Download as CSV file: xf-naca1412-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1412
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7892 0.08134 0.07563 -0.0333 1.0000 0.0450
-12.500 -0.8337 0.06943 0.06352 -0.0428 1.0000 0.0444
-12.250 -0.8670 0.06166 0.05550 -0.0482 1.0000 0.0442
-12.000 -0.8936 0.05628 0.04984 -0.0501 1.0000 0.0444
-11.750 -0.9159 0.05228 0.04554 -0.0493 1.0000 0.0447
-11.500 -0.9339 0.04899 0.04190 -0.0468 1.0000 0.0453
-11.250 -0.9399 0.04608 0.03868 -0.0449 1.0000 0.0461
-11.000 -0.9304 0.04435 0.03691 -0.0437 1.0000 0.0471
-10.750 -0.9220 0.04257 0.03500 -0.0422 1.0000 0.0481
-10.500 -0.9133 0.04071 0.03296 -0.0407 1.0000 0.0493
-10.250 -0.9038 0.03888 0.03086 -0.0391 1.0000 0.0508
-10.000 -0.8933 0.03697 0.02864 -0.0374 1.0000 0.0525
-9.750 -0.8815 0.03509 0.02638 -0.0357 1.0000 0.0540
-9.500 -0.8656 0.03344 0.02465 -0.0344 1.0000 0.0553
-9.250 -0.8488 0.03225 0.02343 -0.0332 1.0000 0.0569
-8.750 -0.8146 0.02993 0.02083 -0.0304 1.0000 0.0610
-8.500 -0.7967 0.02870 0.01938 -0.0290 1.0000 0.0629
-8.250 -0.7784 0.02749 0.01804 -0.0276 1.0000 0.0646
-8.000 -0.7607 0.02650 0.01709 -0.0262 1.0000 0.0668
-7.750 -0.7423 0.02565 0.01619 -0.0248 1.0000 0.0696
-7.500 -0.7235 0.02479 0.01521 -0.0234 1.0000 0.0727
-7.250 -0.7047 0.02390 0.01423 -0.0219 1.0000 0.0756
-7.000 -0.6869 0.02304 0.01341 -0.0204 1.0000 0.0787
-6.750 -0.6683 0.02232 0.01264 -0.0189 1.0000 0.0829
-6.500 -0.6494 0.02162 0.01189 -0.0174 1.0000 0.0884
-6.250 -0.6310 0.02094 0.01125 -0.0160 1.0000 0.0947
-6.000 -0.6119 0.02031 0.01060 -0.0145 1.0000 0.1025
-5.750 -0.5927 0.01972 0.01001 -0.0132 1.0000 0.1117
-5.500 -0.5733 0.01915 0.00950 -0.0119 1.0000 0.1232
-5.250 -0.5533 0.01865 0.00905 -0.0108 1.0000 0.1378
-5.000 -0.5331 0.01820 0.00865 -0.0096 1.0000 0.1552
-4.750 -0.5125 0.01778 0.00829 -0.0086 1.0000 0.1758
-4.500 -0.4918 0.01737 0.00801 -0.0076 1.0000 0.2002
-4.250 -0.4709 0.01701 0.00777 -0.0067 1.0000 0.2287
-4.000 -0.4345 0.01662 0.00752 -0.0090 0.9945 0.2691
-3.750 -0.3982 0.01622 0.00730 -0.0111 0.9879 0.3101
-3.500 -0.3612 0.01588 0.00711 -0.0133 0.9815 0.3523
-3.250 -0.3252 0.01555 0.00694 -0.0152 0.9741 0.3964
-3.000 -0.2904 0.01523 0.00680 -0.0167 0.9663 0.4425
-2.750 -0.2532 0.01492 0.00669 -0.0187 0.9595 0.4937
-2.500 -0.2204 0.01464 0.00660 -0.0196 0.9502 0.5441
-2.250 -0.1822 0.01439 0.00653 -0.0214 0.9439 0.5972
-2.000 -0.1517 0.01417 0.00648 -0.0216 0.9331 0.6440
-1.750 -0.1182 0.01399 0.00644 -0.0221 0.9241 0.6895
-1.500 -0.0849 0.01384 0.00641 -0.0226 0.9143 0.7327
-1.250 -0.0539 0.01374 0.00641 -0.0225 0.9030 0.7724
-1.000 -0.0200 0.01366 0.00639 -0.0229 0.8928 0.8095
-0.750 0.0145 0.01361 0.00637 -0.0234 0.8813 0.8420
-0.500 0.0494 0.01360 0.00637 -0.0240 0.8682 0.8702
-0.250 0.0856 0.01359 0.00634 -0.0250 0.8547 0.8954
0.000 0.1252 0.01357 0.00630 -0.0268 0.8405 0.9161
0.250 0.1648 0.01355 0.00624 -0.0286 0.8249 0.9347
0.500 0.2051 0.01354 0.00617 -0.0306 0.8078 0.9511
0.750 0.2473 0.01351 0.00608 -0.0331 0.7891 0.9651
1.000 0.2905 0.01347 0.00597 -0.0359 0.7689 0.9775
1.250 0.3334 0.01344 0.00587 -0.0388 0.7471 0.9890
1.500 0.3762 0.01342 0.00578 -0.0417 0.7238 0.9997
1.750 0.3996 0.01344 0.00571 -0.0408 0.7022 1.0000
2.000 0.4222 0.01350 0.00569 -0.0397 0.6800 1.0000
2.250 0.4447 0.01359 0.00569 -0.0386 0.6575 1.0000
2.500 0.4674 0.01370 0.00571 -0.0374 0.6353 1.0000
2.750 0.4897 0.01384 0.00577 -0.0363 0.6119 1.0000
3.000 0.5121 0.01400 0.00584 -0.0351 0.5891 1.0000
3.250 0.5344 0.01419 0.00596 -0.0339 0.5664 1.0000
3.500 0.5566 0.01439 0.00609 -0.0327 0.5434 1.0000
3.750 0.5787 0.01463 0.00623 -0.0315 0.5205 1.0000
4.000 0.6006 0.01487 0.00642 -0.0303 0.4958 1.0000
4.250 0.6221 0.01514 0.00661 -0.0290 0.4707 1.0000
4.500 0.6435 0.01543 0.00683 -0.0277 0.4444 1.0000
4.750 0.6649 0.01575 0.00708 -0.0264 0.4182 1.0000
5.000 0.6859 0.01610 0.00734 -0.0251 0.3915 1.0000
5.250 0.7069 0.01647 0.00765 -0.0238 0.3627 1.0000
5.500 0.7273 0.01691 0.00798 -0.0225 0.3310 1.0000
5.750 0.7468 0.01742 0.00833 -0.0211 0.2961 1.0000
6.000 0.7663 0.01799 0.00874 -0.0197 0.2597 1.0000
6.250 0.7856 0.01862 0.00923 -0.0184 0.2256 1.0000
6.500 0.8049 0.01929 0.00976 -0.0171 0.1957 1.0000
6.750 0.8239 0.02000 0.01035 -0.0159 0.1704 1.0000
7.000 0.8431 0.02073 0.01100 -0.0146 0.1482 1.0000
7.250 0.8617 0.02153 0.01173 -0.0133 0.1299 1.0000
7.500 0.8798 0.02237 0.01250 -0.0120 0.1147 1.0000
7.750 0.8979 0.02321 0.01332 -0.0106 0.1023 1.0000
8.000 0.9157 0.02407 0.01421 -0.0092 0.0932 1.0000
8.250 0.9317 0.02508 0.01516 -0.0077 0.0868 1.0000
8.500 0.9492 0.02599 0.01618 -0.0062 0.0810 1.0000
8.750 0.9648 0.02701 0.01719 -0.0047 0.0765 1.0000
9.000 0.9812 0.02804 0.01828 -0.0032 0.0725 1.0000
9.250 0.9976 0.02904 0.01937 -0.0018 0.0689 1.0000
9.500 1.0130 0.03014 0.02051 -0.0003 0.0664 1.0000
9.750 1.0275 0.03144 0.02177 0.0012 0.0644 1.0000
10.000 1.0443 0.03262 0.02313 0.0025 0.0623 1.0000
10.250 1.0600 0.03385 0.02450 0.0039 0.0600 1.0000
10.500 1.0743 0.03508 0.02582 0.0053 0.0579 1.0000
10.750 1.0871 0.03634 0.02714 0.0069 0.0562 1.0000
11.000 1.1011 0.03785 0.02865 0.0082 0.0548 1.0000
11.250 1.1134 0.03949 0.03048 0.0097 0.0536 1.0000
11.500 1.1226 0.04117 0.03241 0.0114 0.0521 1.0000
11.750 1.1300 0.04290 0.03435 0.0131 0.0506 1.0000
12.000 1.1362 0.04467 0.03629 0.0147 0.0493 1.0000
12.250 1.1419 0.04653 0.03829 0.0162 0.0482 1.0000
12.500 1.1475 0.04846 0.04032 0.0174 0.0472 1.0000
12.750 1.1542 0.05051 0.04240 0.0184 0.0463 1.0000
13.000 1.1515 0.05326 0.04538 0.0195 0.0455 1.0000
13.250 1.1423 0.05653 0.04898 0.0203 0.0447 1.0000
13.500 1.1310 0.06025 0.05299 0.0204 0.0441 1.0000
13.750 1.1176 0.06447 0.05750 0.0198 0.0435 1.0000
14.000 1.1015 0.06936 0.06265 0.0184 0.0430 1.0000
14.250 1.0813 0.07516 0.06871 0.0160 0.0427 1.0000
14.500 1.0555 0.08236 0.07616 0.0122 0.0426 1.0000
14.750 1.0196 0.09202 0.08609 0.0062 0.0429 1.0000
15.000 0.9602 0.10790 0.10227 -0.0044 0.0437 1.0000
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