NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64A410 (naca64a410-il) Reynolds number: 50,000 Max Cl/Cd: 37.52 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a410-il-50000-n5.txt Download as CSV file: xf-naca64a410-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A410
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3381 0.09549 0.08886 -0.0425 1.0000 0.0688
-9.250 -0.3417 0.09171 0.08513 -0.0427 1.0000 0.0665
-9.000 -0.4415 0.09582 0.08886 -0.0447 1.0000 0.0604
-8.750 -0.4357 0.09256 0.08563 -0.0435 1.0000 0.0580
-8.500 -0.4406 0.08905 0.08222 -0.0440 1.0000 0.0564
-8.250 -0.4510 0.08563 0.07892 -0.0444 1.0000 0.0551
-7.750 -0.4915 0.07518 0.06846 -0.0513 1.0000 0.0490
-7.500 -0.4939 0.07188 0.06516 -0.0504 1.0000 0.0486
-7.250 -0.4977 0.06839 0.06160 -0.0498 1.0000 0.0484
-7.000 -0.5003 0.06474 0.05780 -0.0495 1.0000 0.0484
-6.750 -0.5004 0.06095 0.05378 -0.0493 1.0000 0.0486
-6.500 -0.4972 0.05712 0.04960 -0.0492 1.0000 0.0489
-6.000 -0.4793 0.04979 0.04164 -0.0486 1.0000 0.0495
-5.750 -0.4651 0.04647 0.03788 -0.0482 1.0000 0.0493
-5.500 -0.4488 0.04319 0.03418 -0.0479 1.0000 0.0494
-5.250 -0.4306 0.04007 0.03067 -0.0476 1.0000 0.0498
-5.000 -0.4114 0.03757 0.02793 -0.0474 1.0000 0.0514
-4.750 -0.3909 0.03567 0.02575 -0.0471 1.0000 0.0546
-4.500 -0.3677 0.03357 0.02320 -0.0468 1.0000 0.0571
-4.250 -0.3428 0.03155 0.02074 -0.0464 1.0000 0.0585
-4.000 -0.3174 0.02986 0.01864 -0.0459 1.0000 0.0603
-3.750 -0.2868 0.02845 0.01716 -0.0467 0.9973 0.0647
-3.500 -0.2521 0.02737 0.01580 -0.0481 0.9930 0.0715
-3.250 -0.2180 0.02639 0.01477 -0.0495 0.9883 0.0772
-3.000 -0.1833 0.02572 0.01396 -0.0512 0.9832 0.0899
-2.750 -0.1475 0.02494 0.01299 -0.0531 0.9780 0.1084
-2.500 -0.1108 0.02357 0.01190 -0.0559 0.9736 0.1619
-2.250 -0.0845 0.02143 0.01193 -0.0561 0.9696 0.6052
-2.000 -0.0615 0.02135 0.01213 -0.0536 0.9636 0.7529
-1.750 -0.0464 0.02103 0.01209 -0.0490 0.9559 0.8678
-1.500 0.0069 0.02098 0.01177 -0.0538 0.9505 1.0000
-1.250 0.0375 0.02113 0.01160 -0.0555 0.9417 1.0000
-1.000 0.0774 0.02138 0.01152 -0.0588 0.9361 1.0000
-0.750 0.1064 0.02159 0.01147 -0.0600 0.9271 1.0000
-0.500 0.1453 0.02186 0.01150 -0.0629 0.9214 1.0000
-0.250 0.1729 0.02212 0.01158 -0.0636 0.9123 1.0000
0.000 0.2106 0.02239 0.01167 -0.0661 0.9065 1.0000
0.250 0.2375 0.02269 0.01184 -0.0666 0.8974 1.0000
0.500 0.2734 0.02297 0.01201 -0.0687 0.8914 1.0000
0.750 0.3005 0.02329 0.01226 -0.0692 0.8824 1.0000
1.000 0.3334 0.02360 0.01249 -0.0706 0.8758 1.0000
1.500 0.3915 0.02426 0.01311 -0.0721 0.8599 1.0000
1.750 0.4207 0.02461 0.01346 -0.0728 0.8521 1.0000
2.000 0.4481 0.02498 0.01385 -0.0731 0.8439 1.0000
2.250 0.4784 0.02531 0.01422 -0.0740 0.8367 1.0000
2.500 0.5033 0.02574 0.01473 -0.0739 0.8277 1.0000
2.750 0.5355 0.02599 0.01507 -0.0749 0.8210 1.0000
3.000 0.5590 0.02640 0.01556 -0.0744 0.8104 1.0000
3.250 0.5882 0.02659 0.01589 -0.0746 0.8008 1.0000
3.500 0.6226 0.02651 0.01596 -0.0753 0.7915 1.0000
3.750 0.6493 0.02658 0.01617 -0.0748 0.7787 1.0000
4.000 0.6775 0.02652 0.01628 -0.0742 0.7654 1.0000
4.250 0.7059 0.02643 0.01641 -0.0737 0.7520 1.0000
4.500 0.7345 0.02629 0.01648 -0.0730 0.7383 1.0000
4.750 0.7639 0.02601 0.01643 -0.0722 0.7232 1.0000
5.000 0.7981 0.02517 0.01587 -0.0713 0.7039 1.0000
5.250 0.8211 0.02449 0.01537 -0.0685 0.6709 1.0000
5.500 0.8435 0.02379 0.01479 -0.0654 0.6268 1.0000
5.750 0.8637 0.02342 0.01446 -0.0623 0.5697 1.0000
6.000 0.8803 0.02346 0.01429 -0.0588 0.4706 1.0000
6.250 0.8807 0.02521 0.01463 -0.0538 0.2677 1.0000
6.500 0.8796 0.02775 0.01631 -0.0504 0.1660 1.0000
6.750 0.8831 0.03005 0.01813 -0.0476 0.1251 1.0000
7.000 0.8909 0.03191 0.01993 -0.0451 0.1000 1.0000
7.250 0.9028 0.03351 0.02157 -0.0430 0.0852 1.0000
7.500 0.9177 0.03485 0.02297 -0.0414 0.0740 1.0000
7.750 0.9340 0.03624 0.02445 -0.0398 0.0664 1.0000
8.000 0.9542 0.03784 0.02609 -0.0387 0.0621 1.0000
8.250 0.9842 0.03952 0.02800 -0.0384 0.0566 1.0000
8.500 1.0168 0.04179 0.03017 -0.0390 0.0516 1.0000
8.750 1.0530 0.04443 0.03327 -0.0395 0.0494 1.0000
9.000 1.0809 0.04751 0.03684 -0.0392 0.0478 1.0000
9.250 1.1007 0.05078 0.04056 -0.0383 0.0465 1.0000
9.500 1.1134 0.05391 0.04410 -0.0367 0.0449 1.0000
9.750 1.1224 0.05686 0.04733 -0.0351 0.0432 1.0000
10.000 1.1282 0.05995 0.05066 -0.0333 0.0417 1.0000
10.250 1.1308 0.06359 0.05454 -0.0315 0.0407 1.0000
10.500 1.1281 0.06746 0.05873 -0.0293 0.0404 1.0000
10.750 1.1196 0.07114 0.06271 -0.0267 0.0403 1.0000
11.000 1.1073 0.07482 0.06668 -0.0242 0.0402 1.0000
11.250 1.0920 0.07858 0.07071 -0.0221 0.0403 1.0000
11.500 1.0740 0.08258 0.07497 -0.0208 0.0404 1.0000
11.750 1.0530 0.08701 0.07966 -0.0204 0.0406 1.0000
12.000 1.0289 0.09226 0.08516 -0.0213 0.0409 1.0000
12.250 1.0004 0.09893 0.09205 -0.0241 0.0414 1.0000
12.500 0.9571 0.10982 0.10315 -0.0314 0.0427 1.0000
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Polar data table (+)
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