NACA 1412 (naca1412-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1412 (naca1412-il) Reynolds number: 200,000 Max Cl/Cd: 57.6 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1412-il-200000.txt Download as CSV file: xf-naca1412-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.8958 0.06212 0.05756 -0.0507 1.0000 0.0460
-12.250 -0.9216 0.05755 0.05277 -0.0514 1.0000 0.0459
-12.000 -0.9456 0.05347 0.04846 -0.0497 1.0000 0.0461
-11.750 -0.9589 0.04964 0.04446 -0.0477 1.0000 0.0466
-11.500 -0.9498 0.04782 0.04266 -0.0468 1.0000 0.0477
-11.250 -0.9376 0.04652 0.04136 -0.0457 1.0000 0.0489
-11.000 -0.9383 0.04388 0.03849 -0.0438 1.0000 0.0498
-10.750 -0.9376 0.04113 0.03545 -0.0417 1.0000 0.0507
-10.500 -0.9341 0.03867 0.03265 -0.0395 1.0000 0.0520
-10.250 -0.9285 0.03652 0.03010 -0.0372 1.0000 0.0534
-10.000 -0.9203 0.03482 0.02800 -0.0347 1.0000 0.0544
-9.750 -0.9080 0.03178 0.02483 -0.0334 1.0000 0.0559
-9.500 -0.8908 0.03059 0.02361 -0.0321 1.0000 0.0575
-9.250 -0.8739 0.02950 0.02243 -0.0306 1.0000 0.0593
-9.000 -0.8574 0.02825 0.02099 -0.0289 1.0000 0.0611
-8.750 -0.8403 0.02701 0.01950 -0.0272 1.0000 0.0627
-8.500 -0.8227 0.02623 0.01847 -0.0254 1.0000 0.0641
-8.250 -0.8043 0.02418 0.01642 -0.0242 1.0000 0.0663
-8.000 -0.7849 0.02326 0.01548 -0.0229 1.0000 0.0682
-7.750 -0.7655 0.02239 0.01454 -0.0215 1.0000 0.0702
-7.500 -0.7459 0.02164 0.01367 -0.0200 1.0000 0.0727
-7.250 -0.7260 0.02100 0.01289 -0.0185 1.0000 0.0748
-7.000 -0.7068 0.01971 0.01163 -0.0171 1.0000 0.0774
-6.750 -0.6874 0.01898 0.01093 -0.0157 1.0000 0.0804
-6.500 -0.6676 0.01838 0.01029 -0.0143 1.0000 0.0840
-6.250 -0.6477 0.01774 0.00960 -0.0129 1.0000 0.0883
-6.000 -0.6287 0.01701 0.00895 -0.0115 1.0000 0.0940
-5.750 -0.6083 0.01649 0.00838 -0.0102 1.0000 0.1012
-5.500 -0.5887 0.01583 0.00781 -0.0089 1.0000 0.1118
-5.250 -0.5684 0.01527 0.00733 -0.0078 1.0000 0.1270
-5.000 -0.5474 0.01476 0.00693 -0.0068 1.0000 0.1469
-4.750 -0.5258 0.01434 0.00663 -0.0060 1.0000 0.1705
-4.500 -0.5038 0.01396 0.00639 -0.0053 1.0000 0.1967
-4.250 -0.4816 0.01365 0.00621 -0.0046 1.0000 0.2260
-4.000 -0.4594 0.01338 0.00609 -0.0041 1.0000 0.2587
-3.750 -0.4189 0.01306 0.00597 -0.0071 0.9955 0.3055
-3.500 -0.3783 0.01272 0.00587 -0.0102 0.9901 0.3588
-3.250 -0.3367 0.01239 0.00580 -0.0133 0.9846 0.4185
-3.000 -0.2984 0.01206 0.00571 -0.0157 0.9777 0.4747
-2.750 -0.2566 0.01176 0.00564 -0.0186 0.9723 0.5326
-2.500 -0.2208 0.01147 0.00557 -0.0201 0.9640 0.5859
-2.250 -0.1788 0.01120 0.00551 -0.0228 0.9591 0.6417
-2.000 -0.1450 0.01096 0.00547 -0.0237 0.9499 0.6916
-1.750 -0.1036 0.01073 0.00541 -0.0259 0.9449 0.7411
-1.500 -0.0721 0.01055 0.00537 -0.0259 0.9349 0.7827
-1.250 -0.0345 0.01038 0.00530 -0.0270 0.9287 0.8200
-1.000 -0.0054 0.01029 0.00528 -0.0263 0.9170 0.8520
-0.750 0.0267 0.01023 0.00524 -0.0261 0.9068 0.8805
-0.500 0.0614 0.01017 0.00519 -0.0264 0.8968 0.9043
-0.250 0.0934 0.01017 0.00516 -0.0263 0.8830 0.9261
0.000 0.1299 0.01017 0.00513 -0.0272 0.8688 0.9430
0.250 0.1722 0.01018 0.00508 -0.0294 0.8535 0.9553
0.500 0.2180 0.01017 0.00501 -0.0324 0.8365 0.9651
0.750 0.2626 0.01015 0.00491 -0.0354 0.8178 0.9753
1.000 0.3073 0.01014 0.00482 -0.0385 0.7971 0.9853
1.250 0.3533 0.01012 0.00472 -0.0421 0.7733 0.9948
1.500 0.3914 0.01010 0.00457 -0.0442 0.7496 1.0000
1.750 0.4143 0.01009 0.00446 -0.0433 0.7245 1.0000
2.000 0.4375 0.01012 0.00437 -0.0423 0.7012 1.0000
2.250 0.4606 0.01018 0.00434 -0.0414 0.6769 1.0000
2.500 0.4835 0.01027 0.00432 -0.0405 0.6541 1.0000
2.750 0.5064 0.01038 0.00434 -0.0395 0.6308 1.0000
3.000 0.5290 0.01052 0.00438 -0.0384 0.6071 1.0000
3.250 0.5515 0.01067 0.00444 -0.0373 0.5830 1.0000
3.500 0.5739 0.01084 0.00452 -0.0362 0.5588 1.0000
3.750 0.5962 0.01104 0.00462 -0.0350 0.5361 1.0000
4.000 0.6185 0.01123 0.00476 -0.0339 0.5126 1.0000
4.250 0.6404 0.01147 0.00489 -0.0327 0.4894 1.0000
4.500 0.6621 0.01169 0.00506 -0.0314 0.4621 1.0000
4.750 0.6831 0.01195 0.00521 -0.0301 0.4312 1.0000
5.000 0.7039 0.01225 0.00539 -0.0287 0.3987 1.0000
5.250 0.7246 0.01258 0.00560 -0.0274 0.3669 1.0000
5.500 0.7452 0.01294 0.00586 -0.0260 0.3349 1.0000
5.750 0.7654 0.01337 0.00615 -0.0246 0.3010 1.0000
6.000 0.7850 0.01387 0.00648 -0.0232 0.2662 1.0000
6.250 0.8047 0.01443 0.00689 -0.0219 0.2313 1.0000
6.500 0.8241 0.01504 0.00735 -0.0205 0.1973 1.0000
6.750 0.8430 0.01576 0.00789 -0.0191 0.1655 1.0000
7.000 0.8611 0.01658 0.00855 -0.0176 0.1375 1.0000
7.250 0.8782 0.01751 0.00931 -0.0160 0.1155 1.0000
7.500 0.8950 0.01850 0.01017 -0.0143 0.1005 1.0000
7.750 0.9147 0.01924 0.01093 -0.0129 0.0910 1.0000
8.000 0.9322 0.02024 0.01190 -0.0114 0.0850 1.0000
8.250 0.9519 0.02104 0.01274 -0.0101 0.0802 1.0000
8.500 0.9696 0.02216 0.01377 -0.0087 0.0763 1.0000
8.750 0.9897 0.02311 0.01480 -0.0075 0.0733 1.0000
9.000 1.0101 0.02396 0.01573 -0.0064 0.0704 1.0000
9.250 1.0304 0.02492 0.01672 -0.0054 0.0681 1.0000
9.500 1.0508 0.02609 0.01786 -0.0045 0.0659 1.0000
9.750 1.0720 0.02771 0.01952 -0.0038 0.0637 1.0000
10.000 1.0916 0.02868 0.02066 -0.0027 0.0620 1.0000
10.250 1.1112 0.02986 0.02198 -0.0016 0.0603 1.0000
10.500 1.1299 0.03102 0.02325 -0.0005 0.0584 1.0000
10.750 1.1485 0.03219 0.02445 0.0004 0.0566 1.0000
11.000 1.1695 0.03467 0.02694 0.0006 0.0547 1.0000
11.250 1.1823 0.03617 0.02870 0.0024 0.0537 1.0000
11.500 1.1932 0.03763 0.03044 0.0043 0.0524 1.0000
11.750 1.2031 0.03923 0.03227 0.0062 0.0509 1.0000
12.000 1.2129 0.04081 0.03401 0.0080 0.0496 1.0000
12.250 1.2203 0.04240 0.03573 0.0100 0.0484 1.0000
12.500 1.2289 0.04406 0.03743 0.0117 0.0473 1.0000
12.750 1.2360 0.04787 0.04135 0.0126 0.0460 1.0000
13.000 1.2237 0.04994 0.04370 0.0161 0.0456 1.0000
13.250 1.2098 0.05241 0.04647 0.0188 0.0451 1.0000
13.500 1.1939 0.05557 0.04991 0.0206 0.0447 1.0000
13.750 1.1756 0.05939 0.05401 0.0214 0.0443 1.0000
14.000 1.1544 0.06401 0.05889 0.0211 0.0441 1.0000
14.250 1.1301 0.06953 0.06467 0.0196 0.0441 1.0000
14.500 1.1021 0.07617 0.07155 0.0167 0.0441 1.0000
14.750 1.0699 0.08419 0.07981 0.0122 0.0444 1.0000
15.000 1.0334 0.09389 0.08971 0.0062 0.0448 1.0000
15.250 0.9931 0.10542 0.10140 -0.0010 0.0454 1.0000
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