NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(1)-412 (naca651412-il) Reynolds number: 50,000 Max Cl/Cd: 30.71 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca651412-il-50000-n5.txt Download as CSV file: xf-naca651412-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-412
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4292 0.10970 0.10229 -0.0463 1.0000 0.0657
-10.500 -0.4275 0.10574 0.09837 -0.0472 1.0000 0.0636
-10.000 -0.4622 0.09168 0.08453 -0.0586 1.0000 0.0556
-9.750 -0.4657 0.08770 0.08062 -0.0594 1.0000 0.0552
-9.500 -0.4749 0.08379 0.07677 -0.0603 1.0000 0.0550
-9.250 -0.4871 0.08035 0.07341 -0.0603 1.0000 0.0546
-9.000 -0.5058 0.07747 0.07060 -0.0592 1.0000 0.0543
-8.750 -0.5249 0.07488 0.06806 -0.0572 1.0000 0.0541
-8.500 -0.5435 0.07227 0.06547 -0.0550 1.0000 0.0539
-8.250 -0.5596 0.06976 0.06293 -0.0524 1.0000 0.0537
-8.000 -0.5750 0.06715 0.06024 -0.0498 1.0000 0.0536
-7.750 -0.5870 0.06446 0.05742 -0.0474 1.0000 0.0536
-7.500 -0.5963 0.06161 0.05437 -0.0451 1.0000 0.0538
-7.250 -0.6009 0.05869 0.05122 -0.0431 1.0000 0.0538
-7.000 -0.6019 0.05571 0.04795 -0.0413 1.0000 0.0539
-6.750 -0.5906 0.05215 0.04400 -0.0416 0.9971 0.0537
-6.500 -0.5671 0.04821 0.03949 -0.0436 0.9909 0.0537
-6.250 -0.5402 0.04471 0.03540 -0.0456 0.9853 0.0541
-6.000 -0.5131 0.04191 0.03193 -0.0469 0.9789 0.0558
-5.750 -0.4849 0.03925 0.02910 -0.0486 0.9741 0.0583
-5.500 -0.4567 0.03710 0.02661 -0.0494 0.9685 0.0598
-5.250 -0.4239 0.03510 0.02422 -0.0507 0.9640 0.0613
-5.000 -0.3954 0.03353 0.02236 -0.0510 0.9583 0.0638
-4.750 -0.3637 0.03233 0.02077 -0.0517 0.9533 0.0679
-4.500 -0.3307 0.03095 0.01939 -0.0525 0.9497 0.0714
-4.250 -0.3065 0.03004 0.01838 -0.0518 0.9433 0.0746
-4.000 -0.2766 0.02925 0.01739 -0.0521 0.9382 0.0805
-3.750 -0.2474 0.02836 0.01648 -0.0529 0.9334 0.0889
-3.500 -0.2238 0.02767 0.01562 -0.0526 0.9267 0.0971
-3.250 -0.1936 0.02669 0.01471 -0.0540 0.9219 0.1161
-3.000 -0.1697 0.02518 0.01376 -0.0548 0.9161 0.1909
-2.750 -0.1654 0.02380 0.01466 -0.0494 0.9098 0.6499
-2.500 -0.1509 0.02466 0.01560 -0.0438 0.9047 0.7510
-2.250 -0.1528 0.02548 0.01647 -0.0348 0.8964 0.8139
-2.000 -0.1349 0.02626 0.01717 -0.0286 0.8922 0.8745
-1.750 -0.1047 0.02625 0.01688 -0.0294 0.8874 0.8877
-1.500 -0.0803 0.02620 0.01660 -0.0295 0.8810 0.8985
-1.250 -0.0435 0.02617 0.01632 -0.0318 0.8769 0.9074
-1.000 -0.0129 0.02617 0.01613 -0.0331 0.8718 0.9167
-0.750 0.0149 0.02620 0.01600 -0.0340 0.8659 0.9272
-0.500 0.0556 0.02623 0.01586 -0.0372 0.8622 0.9352
-0.250 0.0922 0.02630 0.01580 -0.0398 0.8577 0.9441
0.000 0.1236 0.02643 0.01584 -0.0416 0.8517 0.9542
0.250 0.1675 0.02653 0.01584 -0.0456 0.8480 0.9620
0.500 0.2146 0.02662 0.01585 -0.0500 0.8451 0.9689
0.750 0.2465 0.02689 0.01610 -0.0523 0.8384 0.9801
1.000 0.2891 0.02704 0.01623 -0.0562 0.8339 0.9893
1.250 0.3337 0.02717 0.01636 -0.0603 0.8307 0.9999
1.750 0.3477 0.02765 0.01683 -0.0550 0.8156 1.0000
2.000 0.3471 0.02811 0.01726 -0.0514 0.8062 1.0000
2.250 0.3759 0.02837 0.01753 -0.0523 0.8014 1.0000
2.500 0.3897 0.02890 0.01806 -0.0511 0.7936 1.0000
2.750 0.4167 0.02927 0.01849 -0.0518 0.7879 1.0000
3.000 0.4440 0.02968 0.01894 -0.0524 0.7824 1.0000
3.250 0.4631 0.03027 0.01958 -0.0520 0.7744 1.0000
3.500 0.4992 0.03051 0.01994 -0.0537 0.7702 1.0000
3.750 0.5128 0.03125 0.02075 -0.0524 0.7602 1.0000
4.000 0.5494 0.03143 0.02108 -0.0540 0.7554 1.0000
4.250 0.5641 0.03219 0.02196 -0.0528 0.7450 1.0000
4.750 0.6174 0.03302 0.02312 -0.0532 0.7288 1.0000
5.000 0.6422 0.03339 0.02368 -0.0529 0.7186 1.0000
5.250 0.6827 0.03305 0.02364 -0.0540 0.7108 1.0000
5.500 0.7051 0.03328 0.02410 -0.0531 0.6977 1.0000
5.750 0.7314 0.03325 0.02434 -0.0523 0.6844 1.0000
6.000 0.7913 0.02812 0.01953 -0.0494 0.6337 1.0000
6.250 0.7991 0.02666 0.01808 -0.0435 0.5671 1.0000
6.500 0.8105 0.02639 0.01784 -0.0397 0.4931 1.0000
6.750 0.8184 0.02711 0.01672 -0.0344 0.2474 1.0000
7.000 0.8093 0.02981 0.01861 -0.0308 0.1536 1.0000
7.250 0.8094 0.03212 0.02055 -0.0284 0.1153 1.0000
7.500 0.8152 0.03408 0.02234 -0.0265 0.0969 1.0000
7.750 0.8247 0.03582 0.02406 -0.0249 0.0858 1.0000
8.000 0.8361 0.03754 0.02576 -0.0235 0.0791 1.0000
8.250 0.8529 0.03896 0.02731 -0.0223 0.0720 1.0000
8.500 0.8740 0.04041 0.02878 -0.0214 0.0662 1.0000
8.750 0.9135 0.04155 0.03016 -0.0215 0.0613 1.0000
9.000 0.9569 0.04325 0.03184 -0.0228 0.0563 1.0000
9.250 0.9997 0.04552 0.03447 -0.0242 0.0525 1.0000
9.500 1.0375 0.04845 0.03782 -0.0254 0.0506 1.0000
9.750 1.0624 0.05145 0.04119 -0.0254 0.0493 1.0000
10.000 1.0791 0.05430 0.04434 -0.0247 0.0478 1.0000
10.250 1.0917 0.05711 0.04737 -0.0238 0.0463 1.0000
10.500 1.1037 0.06059 0.05099 -0.0232 0.0449 1.0000
10.750 1.1007 0.06360 0.05437 -0.0207 0.0443 1.0000
11.000 1.0942 0.06676 0.05790 -0.0182 0.0441 1.0000
11.250 1.0854 0.07019 0.06170 -0.0161 0.0440 1.0000
11.500 1.0735 0.07383 0.06564 -0.0143 0.0439 1.0000
11.750 1.0595 0.07774 0.06982 -0.0131 0.0439 1.0000
12.000 1.0434 0.08199 0.07432 -0.0125 0.0440 1.0000
12.250 1.0258 0.08663 0.07919 -0.0127 0.0441 1.0000
12.500 1.0069 0.09175 0.08451 -0.0136 0.0442 1.0000
12.750 0.9877 0.09733 0.09027 -0.0153 0.0444 1.0000
13.000 0.9690 0.10339 0.09647 -0.0179 0.0445 1.0000
13.250 0.9511 0.10994 0.10311 -0.0211 0.0447 1.0000
13.500 0.8873 0.12695 0.12038 -0.0344 0.0469 1.0000
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Polar data table (+)
Polar graphs
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