NACA 63-412 AIRFOIL (n63412-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-412 AIRFOIL (n63412-il) Reynolds number: 100,000 Max Cl/Cd: 54.83 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n63412-il-100000-n5.txt Download as CSV file: xf-n63412-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4783 0.08951 0.08431 -0.0435 1.0000 0.0331
-10.250 -0.4905 0.08189 0.07675 -0.0480 1.0000 0.0327
-10.000 -0.5183 0.07077 0.06565 -0.0563 1.0000 0.0317
-9.750 -0.5512 0.06300 0.05780 -0.0619 1.0000 0.0311
-9.500 -0.5841 0.05816 0.05286 -0.0629 1.0000 0.0306
-9.250 -0.6054 0.05429 0.04882 -0.0623 1.0000 0.0305
-9.000 -0.6197 0.05077 0.04510 -0.0608 1.0000 0.0305
-8.750 -0.6276 0.04780 0.04192 -0.0589 1.0000 0.0306
-8.500 -0.6327 0.04510 0.03900 -0.0567 1.0000 0.0309
-8.250 -0.6350 0.04262 0.03627 -0.0543 1.0000 0.0312
-8.000 -0.6320 0.04016 0.03353 -0.0525 0.9994 0.0317
-7.750 -0.6042 0.03712 0.03003 -0.0553 0.9922 0.0335
-7.500 -0.5747 0.03401 0.02632 -0.0577 0.9856 0.0354
-7.250 -0.5451 0.03138 0.02311 -0.0594 0.9786 0.0365
-7.000 -0.5139 0.02893 0.02042 -0.0612 0.9732 0.0378
-6.750 -0.4828 0.02752 0.01891 -0.0629 0.9664 0.0402
-6.500 -0.4482 0.02608 0.01724 -0.0648 0.9617 0.0430
-6.250 -0.4174 0.02465 0.01560 -0.0656 0.9546 0.0449
-6.000 -0.3825 0.02324 0.01405 -0.0673 0.9499 0.0474
-5.750 -0.3523 0.02220 0.01305 -0.0684 0.9426 0.0511
-5.500 -0.3195 0.02124 0.01200 -0.0697 0.9363 0.0551
-5.250 -0.2886 0.02028 0.01096 -0.0706 0.9293 0.0590
-5.000 -0.2581 0.01951 0.01018 -0.0716 0.9217 0.0661
-4.750 -0.2267 0.01870 0.00933 -0.0727 0.9150 0.0745
-4.500 -0.1977 0.01799 0.00862 -0.0734 0.9068 0.0891
-4.250 -0.1667 0.01711 0.00789 -0.0745 0.9003 0.1256
-4.000 -0.1415 0.01578 0.00726 -0.0752 0.8916 0.2573
-3.750 -0.1144 0.01487 0.00712 -0.0757 0.8849 0.4407
-3.500 -0.0882 0.01474 0.00715 -0.0751 0.8763 0.5184
-3.250 -0.0597 0.01473 0.00720 -0.0748 0.8696 0.5748
-3.000 -0.0344 0.01484 0.00734 -0.0738 0.8610 0.6176
-2.750 -0.0073 0.01497 0.00745 -0.0729 0.8543 0.6488
-2.500 0.0176 0.01509 0.00754 -0.0718 0.8457 0.6695
-2.250 0.0463 0.01510 0.00744 -0.0716 0.8393 0.6843
-2.000 0.0725 0.01510 0.00736 -0.0712 0.8305 0.6966
-1.750 0.1018 0.01505 0.00720 -0.0712 0.8244 0.7083
-1.500 0.1269 0.01507 0.00718 -0.0705 0.8155 0.7176
-1.250 0.1558 0.01502 0.00703 -0.0704 0.8093 0.7277
-1.000 0.1813 0.01504 0.00701 -0.0700 0.8003 0.7376
-0.750 0.2092 0.01500 0.00692 -0.0696 0.7941 0.7465
-0.500 0.2351 0.01503 0.00691 -0.0693 0.7852 0.7568
-0.250 0.2622 0.01500 0.00685 -0.0688 0.7788 0.7656
0.000 0.2876 0.01504 0.00689 -0.0683 0.7701 0.7753
0.250 0.3154 0.01503 0.00683 -0.0681 0.7636 0.7855
0.500 0.3399 0.01508 0.00690 -0.0674 0.7551 0.7947
0.750 0.3672 0.01508 0.00687 -0.0671 0.7484 0.8049
1.000 0.3923 0.01514 0.00697 -0.0665 0.7400 0.8154
1.250 0.4185 0.01514 0.00697 -0.0659 0.7333 0.8252
1.500 0.4434 0.01521 0.00708 -0.0653 0.7250 0.8362
1.750 0.4699 0.01523 0.00711 -0.0648 0.7182 0.8476
2.000 0.4939 0.01529 0.00723 -0.0640 0.7099 0.8588
2.250 0.5195 0.01529 0.00727 -0.0633 0.7029 0.8706
2.500 0.5438 0.01535 0.00740 -0.0626 0.6946 0.8834
2.750 0.5695 0.01534 0.00745 -0.0619 0.6874 0.8970
3.000 0.5940 0.01539 0.00759 -0.0612 0.6786 0.9119
3.250 0.6222 0.01536 0.00761 -0.0611 0.6713 0.9278
3.500 0.6518 0.01542 0.00781 -0.0615 0.6616 0.9469
3.750 0.6880 0.01543 0.00790 -0.0632 0.6529 0.9711
4.000 0.7192 0.01553 0.00807 -0.0642 0.6423 1.0000
4.250 0.7467 0.01568 0.00829 -0.0643 0.6301 1.0000
4.500 0.7742 0.01578 0.00844 -0.0643 0.6163 1.0000
4.750 0.8012 0.01585 0.00855 -0.0642 0.5995 1.0000
5.000 0.8279 0.01590 0.00863 -0.0638 0.5803 1.0000
5.250 0.8527 0.01600 0.00877 -0.0632 0.5553 1.0000
5.500 0.8763 0.01611 0.00883 -0.0623 0.5224 1.0000
6.000 0.9189 0.01676 0.00924 -0.0599 0.4276 1.0000
6.250 0.9359 0.01747 0.00961 -0.0583 0.3536 1.0000
6.500 0.9469 0.01877 0.01034 -0.0561 0.2602 1.0000
6.750 0.9566 0.02034 0.01138 -0.0541 0.1783 1.0000
7.000 0.9673 0.02189 0.01254 -0.0523 0.1203 1.0000
7.250 0.9796 0.02327 0.01370 -0.0506 0.0900 1.0000
7.500 0.9931 0.02449 0.01485 -0.0489 0.0736 1.0000
7.750 1.0056 0.02574 0.01605 -0.0472 0.0638 1.0000
8.000 1.0186 0.02687 0.01724 -0.0455 0.0568 1.0000
8.250 1.0281 0.02813 0.01853 -0.0434 0.0522 1.0000
8.500 1.0395 0.02934 0.01984 -0.0416 0.0482 1.0000
8.750 1.0494 0.03070 0.02122 -0.0398 0.0451 1.0000
9.000 1.0595 0.03220 0.02276 -0.0381 0.0426 1.0000
9.250 1.0728 0.03354 0.02423 -0.0368 0.0397 1.0000
9.500 1.0861 0.03501 0.02578 -0.0355 0.0378 1.0000
9.750 1.0998 0.03659 0.02741 -0.0344 0.0363 1.0000
10.000 1.1158 0.03843 0.02925 -0.0335 0.0349 1.0000
10.250 1.1351 0.04023 0.03120 -0.0327 0.0337 1.0000
10.500 1.1522 0.04202 0.03321 -0.0319 0.0322 1.0000
10.750 1.1665 0.04388 0.03527 -0.0310 0.0308 1.0000
11.000 1.1787 0.04583 0.03742 -0.0300 0.0296 1.0000
11.250 1.1908 0.04801 0.03978 -0.0291 0.0288 1.0000
11.500 1.2009 0.05036 0.04230 -0.0282 0.0282 1.0000
11.750 1.2091 0.05293 0.04503 -0.0273 0.0277 1.0000
12.000 1.2152 0.05586 0.04815 -0.0265 0.0273 1.0000
12.250 1.2175 0.05930 0.05178 -0.0256 0.0269 1.0000
12.500 1.2111 0.06277 0.05558 -0.0246 0.0268 1.0000
12.750 1.2019 0.06659 0.05972 -0.0241 0.0266 1.0000
13.000 1.1897 0.07081 0.06425 -0.0240 0.0265 1.0000
13.250 1.1750 0.07547 0.06920 -0.0245 0.0265 1.0000
13.500 1.1579 0.08067 0.07468 -0.0257 0.0264 1.0000
13.750 1.1390 0.08644 0.08071 -0.0276 0.0264 1.0000
14.000 1.1186 0.09282 0.08733 -0.0304 0.0264 1.0000
14.250 1.0970 0.09992 0.09465 -0.0341 0.0264 1.0000
14.500 1.0747 0.10777 0.10271 -0.0387 0.0265 1.0000
14.750 1.0520 0.11657 0.11168 -0.0443 0.0267 1.0000
15.000 1.0291 0.12642 0.12167 -0.0508 0.0269 1.0000
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