NACA 4412 (naca4412-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 4412 (naca4412-il) Reynolds number: 200,000 Max Cl/Cd: 78.14 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4412-il-200000.txt Download as CSV file: xf-naca4412-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4088 0.08983 0.08647 -0.0344 1.0000 0.0813
-8.250 -0.4231 0.08831 0.08501 -0.0315 1.0000 0.0823
-8.000 -0.4442 0.08695 0.08373 -0.0282 1.0000 0.0831
-7.750 -0.4937 0.05313 0.04929 -0.0671 0.9865 0.0673
-7.500 -0.4712 0.04655 0.04243 -0.0720 0.9817 0.0641
-7.250 -0.4535 0.03731 0.03244 -0.0777 0.9755 0.0622
-7.000 -0.4231 0.03226 0.02667 -0.0816 0.9717 0.0637
-6.750 -0.3952 0.02910 0.02295 -0.0831 0.9655 0.0647
-6.500 -0.3582 0.02703 0.02031 -0.0857 0.9620 0.0660
-6.250 -0.3204 0.02462 0.01772 -0.0887 0.9600 0.0684
-6.000 -0.2930 0.02357 0.01656 -0.0890 0.9523 0.0702
-5.750 -0.2544 0.02238 0.01517 -0.0913 0.9489 0.0725
-5.500 -0.2129 0.02134 0.01390 -0.0940 0.9465 0.0756
-5.250 -0.1843 0.02032 0.01270 -0.0942 0.9393 0.0785
-5.000 -0.1466 0.01934 0.01174 -0.0963 0.9352 0.0824
-4.750 -0.1047 0.01855 0.01086 -0.0990 0.9326 0.0877
-4.500 -0.0618 0.01758 0.00989 -0.1020 0.9308 0.0951
-4.250 -0.0351 0.01719 0.00943 -0.1016 0.9217 0.1030
-4.000 0.0030 0.01638 0.00871 -0.1036 0.9180 0.1150
-3.750 0.0426 0.01571 0.00806 -0.1058 0.9151 0.1299
-3.500 0.0687 0.01531 0.00771 -0.1053 0.9057 0.1437
-3.250 0.1047 0.01477 0.00720 -0.1066 0.9011 0.1620
-3.000 0.1342 0.01437 0.00686 -0.1068 0.8934 0.1821
-2.750 0.1659 0.01392 0.00653 -0.1073 0.8865 0.2077
-2.500 0.1964 0.01352 0.00623 -0.1075 0.8792 0.2377
-2.250 0.2255 0.01312 0.00593 -0.1075 0.8706 0.2707
-2.000 0.2541 0.01274 0.00566 -0.1074 0.8618 0.3065
-1.750 0.2836 0.01233 0.00537 -0.1074 0.8533 0.3489
-1.500 0.3098 0.01195 0.00520 -0.1069 0.8424 0.4005
-1.250 0.3373 0.01136 0.00499 -0.1066 0.8336 0.5000
-1.000 0.3583 0.01070 0.00498 -0.1046 0.8222 0.6832
-0.500 0.4431 0.00999 0.00468 -0.1085 0.8021 1.0000
-0.250 0.4683 0.01000 0.00456 -0.1077 0.7890 1.0000
0.000 0.4938 0.01005 0.00448 -0.1071 0.7758 1.0000
0.250 0.5198 0.01011 0.00441 -0.1065 0.7629 1.0000
0.500 0.5464 0.01019 0.00435 -0.1060 0.7504 1.0000
0.750 0.5733 0.01027 0.00429 -0.1056 0.7383 1.0000
1.000 0.5988 0.01039 0.00431 -0.1050 0.7246 1.0000
1.250 0.6247 0.01052 0.00435 -0.1045 0.7115 1.0000
1.500 0.6510 0.01066 0.00439 -0.1040 0.6992 1.0000
1.750 0.6778 0.01082 0.00443 -0.1036 0.6876 1.0000
2.000 0.7038 0.01097 0.00451 -0.1032 0.6752 1.0000
2.250 0.7297 0.01115 0.00463 -0.1027 0.6629 1.0000
2.500 0.7561 0.01133 0.00474 -0.1023 0.6517 1.0000
2.750 0.7828 0.01152 0.00483 -0.1020 0.6409 1.0000
3.000 0.8084 0.01171 0.00500 -0.1014 0.6289 1.0000
3.250 0.8345 0.01191 0.00515 -0.1010 0.6180 1.0000
3.500 0.8613 0.01213 0.00528 -0.1007 0.6079 1.0000
3.750 0.8865 0.01233 0.00549 -0.1002 0.5965 1.0000
4.000 0.9127 0.01256 0.00569 -0.0998 0.5863 1.0000
4.250 0.9390 0.01280 0.00587 -0.0995 0.5765 1.0000
4.500 0.9643 0.01303 0.00613 -0.0990 0.5659 1.0000
4.750 0.9905 0.01330 0.00636 -0.0986 0.5563 1.0000
5.000 1.0156 0.01352 0.00657 -0.0980 0.5448 1.0000
5.250 1.0396 0.01373 0.00679 -0.0972 0.5317 1.0000
5.500 1.0639 0.01396 0.00701 -0.0965 0.5191 1.0000
5.750 1.0888 0.01422 0.00724 -0.0959 0.5080 1.0000
6.000 1.1122 0.01444 0.00743 -0.0950 0.4940 1.0000
6.250 1.1342 0.01464 0.00764 -0.0938 0.4781 1.0000
6.500 1.1562 0.01486 0.00788 -0.0927 0.4627 1.0000
6.750 1.1783 0.01510 0.00815 -0.0916 0.4482 1.0000
7.000 1.2002 0.01536 0.00845 -0.0905 0.4333 1.0000
7.250 1.2215 0.01565 0.00876 -0.0893 0.4177 1.0000
7.500 1.2420 0.01596 0.00908 -0.0880 0.4012 1.0000
7.750 1.2616 0.01630 0.00943 -0.0866 0.3835 1.0000
8.000 1.2799 0.01670 0.00982 -0.0849 0.3635 1.0000
8.250 1.2967 0.01714 0.01026 -0.0831 0.3392 1.0000
8.500 1.3110 0.01772 0.01076 -0.0809 0.3110 1.0000
8.750 1.3218 0.01847 0.01138 -0.0781 0.2773 1.0000
9.000 1.3267 0.01944 0.01217 -0.0745 0.2406 1.0000
9.250 1.3283 0.02069 0.01320 -0.0706 0.1997 1.0000
9.500 1.3275 0.02223 0.01449 -0.0667 0.1617 1.0000
9.750 1.3266 0.02391 0.01597 -0.0630 0.1356 1.0000
10.000 1.3275 0.02555 0.01752 -0.0598 0.1187 1.0000
10.250 1.3289 0.02726 0.01916 -0.0569 0.1080 1.0000
10.500 1.3326 0.02887 0.02077 -0.0544 0.1001 1.0000
10.750 1.3366 0.03055 0.02249 -0.0520 0.0942 1.0000
11.000 1.3429 0.03209 0.02408 -0.0501 0.0890 1.0000
11.250 1.3438 0.03415 0.02607 -0.0479 0.0848 1.0000
11.500 1.3530 0.03558 0.02764 -0.0464 0.0812 1.0000
11.750 1.3601 0.03722 0.02934 -0.0450 0.0776 1.0000
12.000 1.3641 0.03917 0.03125 -0.0433 0.0746 1.0000
12.250 1.3713 0.04092 0.03309 -0.0418 0.0719 1.0000
12.500 1.3790 0.04262 0.03491 -0.0407 0.0690 1.0000
12.750 1.3857 0.04441 0.03676 -0.0395 0.0664 1.0000
13.000 1.3923 0.04629 0.03859 -0.0382 0.0639 1.0000
13.250 1.4001 0.04814 0.04054 -0.0369 0.0616 1.0000
13.500 1.4059 0.05012 0.04268 -0.0360 0.0593 1.0000
13.750 1.4115 0.05212 0.04477 -0.0351 0.0571 1.0000
14.000 1.4180 0.05407 0.04670 -0.0342 0.0549 1.0000
14.250 1.4266 0.05607 0.04875 -0.0329 0.0527 1.0000
14.500 1.4286 0.05852 0.05141 -0.0322 0.0509 1.0000
14.750 1.4308 0.06101 0.05404 -0.0316 0.0491 1.0000
15.000 1.4342 0.06336 0.05644 -0.0312 0.0473 1.0000
15.250 1.4467 0.06514 0.05814 -0.0297 0.0450 1.0000
15.500 1.4416 0.06845 0.06172 -0.0297 0.0440 1.0000
15.750 1.4385 0.07175 0.06524 -0.0296 0.0427 1.0000
16.000 1.4362 0.07501 0.06865 -0.0296 0.0414 1.0000
16.250 1.4351 0.07813 0.07188 -0.0298 0.0401 1.0000
16.500 1.4392 0.08059 0.07434 -0.0296 0.0388 1.0000
16.750 1.4401 0.08377 0.07759 -0.0291 0.0376 1.0000
17.000 1.4274 0.08864 0.08274 -0.0304 0.0369 1.0000
17.250 1.4151 0.09369 0.08804 -0.0318 0.0363 1.0000
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Polar data table (+)
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