NACA 64-215 AIRFOIL (n64215-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: NACA 64-215 AIRFOIL (n64215-il) Reynolds number: 200,000 Max Cl/Cd: 63.13 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64215-il-200000.txt Download as CSV file: xf-n64215-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-215 AIRFOIL
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 -0.6104 0.07197 0.06819 -0.0542 1.0000 0.0523
-12.250 -0.6242 0.06575 0.06193 -0.0559 1.0000 0.0513
-12.000 -0.6493 0.05922 0.05530 -0.0579 1.0000 0.0503
-11.750 -0.6829 0.05277 0.04867 -0.0595 1.0000 0.0492
-11.500 -0.8007 0.05551 0.05083 -0.0586 1.0000 0.0470
-11.250 -0.8511 0.05109 0.04582 -0.0538 1.0000 0.0438
-11.000 -0.8554 0.04773 0.04227 -0.0520 1.0000 0.0435
-10.750 -0.8599 0.04501 0.03927 -0.0497 1.0000 0.0436
-10.500 -0.8596 0.04234 0.03633 -0.0476 1.0000 0.0437
-10.250 -0.8578 0.04011 0.03383 -0.0451 1.0000 0.0439
-10.000 -0.8562 0.03805 0.03155 -0.0421 1.0000 0.0441
-9.750 -0.8598 0.03649 0.02982 -0.0380 1.0000 0.0441
-9.500 -0.8676 0.03542 0.02858 -0.0331 1.0000 0.0442
-9.250 -0.8396 0.03274 0.02556 -0.0347 0.9951 0.0447
-9.000 -0.8051 0.02966 0.02236 -0.0371 0.9908 0.0458
-8.750 -0.7678 0.02813 0.02081 -0.0399 0.9856 0.0478
-8.500 -0.7295 0.02664 0.01919 -0.0426 0.9810 0.0499
-8.250 -0.6916 0.02516 0.01752 -0.0449 0.9756 0.0516
-8.000 -0.6510 0.02363 0.01586 -0.0477 0.9719 0.0535
-7.750 -0.6153 0.02217 0.01451 -0.0499 0.9660 0.0569
-7.500 -0.5784 0.02118 0.01348 -0.0522 0.9594 0.0607
-7.250 -0.5459 0.02003 0.01229 -0.0536 0.9514 0.0641
-7.000 -0.5164 0.01901 0.01134 -0.0547 0.9426 0.0690
-6.750 -0.4922 0.01840 0.01064 -0.0544 0.9310 0.0744
-6.500 -0.4741 0.01751 0.00981 -0.0533 0.9194 0.0811
-6.250 -0.4556 0.01677 0.00907 -0.0520 0.9091 0.0909
-6.000 -0.4395 0.01602 0.00839 -0.0503 0.8973 0.1077
-5.750 -0.4273 0.01483 0.00755 -0.0484 0.8864 0.1645
-5.500 -0.4229 0.01285 0.00664 -0.0458 0.8767 0.3652
-5.250 -0.4044 0.01251 0.00672 -0.0442 0.8665 0.4892
-5.000 -0.3800 0.01256 0.00677 -0.0432 0.8589 0.5274
-4.750 -0.3549 0.01267 0.00679 -0.0424 0.8499 0.5536
-4.500 -0.3291 0.01279 0.00684 -0.0416 0.8432 0.5727
-4.250 -0.3031 0.01291 0.00692 -0.0410 0.8345 0.5889
-4.000 -0.2768 0.01306 0.00697 -0.0403 0.8284 0.6045
-3.750 -0.2509 0.01327 0.00716 -0.0396 0.8197 0.6201
-3.500 -0.2246 0.01350 0.00738 -0.0386 0.8132 0.6342
-3.250 -0.1987 0.01378 0.00769 -0.0377 0.8054 0.6478
-3.000 -0.1725 0.01402 0.00792 -0.0367 0.7985 0.6603
-2.750 -0.1455 0.01407 0.00785 -0.0365 0.7923 0.6704
-2.500 -0.1184 0.01406 0.00785 -0.0362 0.7849 0.6749
-2.250 -0.0906 0.01401 0.00771 -0.0361 0.7794 0.6801
-2.000 -0.0629 0.01394 0.00754 -0.0364 0.7724 0.6867
-1.750 -0.0355 0.01391 0.00750 -0.0361 0.7660 0.6907
-1.500 -0.0076 0.01389 0.00741 -0.0360 0.7611 0.6959
-1.250 0.0201 0.01384 0.00732 -0.0363 0.7535 0.7022
-1.000 0.0480 0.01378 0.00722 -0.0363 0.7480 0.7062
-0.750 0.0759 0.01379 0.00720 -0.0363 0.7431 0.7107
-0.500 0.1036 0.01379 0.00720 -0.0365 0.7366 0.7165
-0.250 0.1320 0.01374 0.00710 -0.0367 0.7317 0.7217
0.000 0.1600 0.01376 0.00711 -0.0367 0.7273 0.7260
0.250 0.1873 0.01380 0.00719 -0.0368 0.7208 0.7316
0.500 0.2158 0.01379 0.00714 -0.0371 0.7158 0.7380
0.750 0.2437 0.01383 0.00718 -0.0369 0.7121 0.7428
1.000 0.2708 0.01393 0.00735 -0.0371 0.7064 0.7489
1.250 0.2989 0.01397 0.00739 -0.0373 0.7014 0.7552
1.500 0.3265 0.01401 0.00745 -0.0372 0.6973 0.7604
1.750 0.3543 0.01412 0.00759 -0.0373 0.6928 0.7674
2.000 0.3810 0.01422 0.00777 -0.0373 0.6873 0.7737
2.250 0.4083 0.01426 0.00785 -0.0371 0.6825 0.7803
2.500 0.4371 0.01432 0.00789 -0.0372 0.6785 0.7881
2.750 0.4619 0.01446 0.00818 -0.0368 0.6723 0.7943
3.000 0.4899 0.01454 0.00830 -0.0369 0.6675 0.8026
3.250 0.5170 0.01459 0.00838 -0.0366 0.6636 0.8089
3.500 0.5427 0.01475 0.00866 -0.0364 0.6576 0.8172
3.750 0.5688 0.01468 0.00865 -0.0358 0.6503 0.8245
4.000 0.5949 0.01461 0.00862 -0.0351 0.6416 0.8334
4.250 0.6211 0.01435 0.00835 -0.0342 0.6312 0.8412
4.500 0.6456 0.01420 0.00828 -0.0333 0.6190 0.8509
4.750 0.6693 0.01401 0.00816 -0.0320 0.6070 0.8589
5.000 0.6944 0.01379 0.00794 -0.0311 0.5929 0.8690
5.250 0.7167 0.01360 0.00779 -0.0295 0.5791 0.8780
5.500 0.7396 0.01347 0.00771 -0.0282 0.5657 0.8884
5.750 0.7612 0.01337 0.00769 -0.0267 0.5502 0.9003
6.000 0.7806 0.01325 0.00764 -0.0247 0.5327 0.9120
6.250 0.7991 0.01314 0.00765 -0.0227 0.5095 0.9254
6.500 0.8178 0.01307 0.00760 -0.0207 0.4779 0.9407
6.750 0.8359 0.01324 0.00759 -0.0190 0.4068 0.9586
7.000 0.8464 0.01516 0.00851 -0.0181 0.2396 0.9819
7.250 0.8493 0.01712 0.00979 -0.0165 0.1376 1.0000
7.500 0.8543 0.01859 0.01093 -0.0144 0.1005 1.0000
7.750 0.8628 0.01971 0.01194 -0.0125 0.0853 1.0000
8.000 0.8700 0.02095 0.01308 -0.0105 0.0766 1.0000
8.250 0.8832 0.02191 0.01406 -0.0092 0.0699 1.0000
8.500 0.8910 0.02329 0.01536 -0.0075 0.0651 1.0000
8.750 0.9051 0.02431 0.01644 -0.0063 0.0612 1.0000
9.000 0.9176 0.02549 0.01758 -0.0052 0.0577 1.0000
9.250 0.9313 0.02685 0.01890 -0.0040 0.0546 1.0000
9.500 0.9481 0.02787 0.01998 -0.0032 0.0517 1.0000
9.750 0.9657 0.02898 0.02109 -0.0024 0.0495 1.0000
10.000 0.9936 0.03062 0.02258 -0.0023 0.0469 1.0000
10.250 1.0137 0.03170 0.02381 -0.0017 0.0456 1.0000
10.500 1.0350 0.03290 0.02512 -0.0012 0.0439 1.0000
10.750 1.0545 0.03413 0.02642 -0.0007 0.0421 1.0000
11.000 1.0775 0.03552 0.02781 -0.0006 0.0406 1.0000
11.250 1.1233 0.03852 0.03083 -0.0029 0.0392 1.0000
11.500 1.1351 0.04022 0.03278 -0.0015 0.0388 1.0000
11.750 1.1460 0.04229 0.03513 -0.0002 0.0384 1.0000
12.000 1.1549 0.04463 0.03774 0.0011 0.0380 1.0000
12.250 1.1585 0.04715 0.04054 0.0027 0.0377 1.0000
12.500 1.1585 0.04981 0.04346 0.0043 0.0373 1.0000
12.750 1.1548 0.05257 0.04648 0.0058 0.0370 1.0000
13.000 1.1478 0.05572 0.04988 0.0071 0.0368 1.0000
13.250 1.1370 0.05916 0.05358 0.0081 0.0365 1.0000
13.500 1.1226 0.06328 0.05796 0.0088 0.0368 1.0000
13.750 1.1044 0.06784 0.06278 0.0089 0.0369 1.0000
14.000 1.0846 0.07285 0.06803 0.0083 0.0372 1.0000
14.250 1.0636 0.07830 0.07369 0.0071 0.0376 1.0000
14.500 1.0401 0.08436 0.07996 0.0050 0.0378 1.0000
14.750 1.0170 0.09089 0.08667 0.0024 0.0382 1.0000
15.000 0.9947 0.09794 0.09386 -0.0009 0.0386 1.0000
15.250 0.9752 0.10536 0.10139 -0.0044 0.0390 1.0000
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