NACA 16-012 (naca16012-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 16-012 (naca16012-il) Reynolds number: 200,000 Max Cl/Cd: 44.87 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16012-il-200000.txt Download as CSV file: xf-naca16012-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-012
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5324 0.09132 0.08798 -0.0454 1.0000 0.0622
-10.750 -0.5524 0.08477 0.08144 -0.0477 1.0000 0.0619
-10.500 -0.5768 0.07887 0.07554 -0.0488 1.0000 0.0614
-10.250 -0.6013 0.07389 0.07053 -0.0484 1.0000 0.0607
-10.000 -0.6296 0.06950 0.06610 -0.0468 1.0000 0.0601
-9.750 -0.6592 0.06582 0.06237 -0.0436 1.0000 0.0595
-9.500 -0.6895 0.06285 0.05934 -0.0388 1.0000 0.0592
-9.250 -0.7199 0.06054 0.05697 -0.0327 1.0000 0.0590
-9.000 -0.7494 0.05862 0.05498 -0.0256 1.0000 0.0589
-8.750 -0.7737 0.05614 0.05238 -0.0194 1.0000 0.0598
-8.500 -0.7985 0.05412 0.05014 -0.0125 1.0000 0.0617
-7.000 -0.8886 0.03808 0.03128 0.0259 1.0000 0.0387
-6.750 -0.8787 0.03449 0.02730 0.0292 1.0000 0.0379
-6.500 -0.8640 0.03184 0.02425 0.0319 1.0000 0.0379
-6.250 -0.8467 0.03003 0.02205 0.0343 1.0000 0.0387
-6.000 -0.8273 0.02764 0.01930 0.0359 1.0000 0.0409
-5.750 -0.8050 0.02587 0.01743 0.0368 1.0000 0.0429
-5.500 -0.7829 0.02465 0.01609 0.0379 1.0000 0.0449
-5.250 -0.7612 0.02368 0.01500 0.0390 1.0000 0.0478
-5.000 -0.7410 0.02318 0.01430 0.0405 1.0000 0.0508
-4.750 -0.7185 0.02150 0.01264 0.0414 1.0000 0.0543
-4.500 -0.6997 0.02081 0.01196 0.0429 1.0000 0.0583
-4.250 -0.6807 0.02036 0.01142 0.0445 1.0000 0.0628
-4.000 -0.6643 0.01942 0.01052 0.0465 1.0000 0.0674
-3.750 -0.6467 0.01895 0.01002 0.0483 1.0000 0.0737
-3.500 -0.6298 0.01836 0.00945 0.0502 1.0000 0.0815
-3.250 -0.6125 0.01783 0.00894 0.0520 1.0000 0.0945
-3.000 -0.5996 0.01661 0.00835 0.0545 1.0000 0.1891
-2.750 -0.6067 0.01353 0.00808 0.0614 0.9997 0.7181
-2.500 -0.5631 0.01483 0.00979 0.0604 0.9992 0.8817
-2.250 -0.5220 0.01600 0.01083 0.0586 0.9973 0.9121
-2.000 -0.4633 0.01764 0.01231 0.0533 0.9976 0.9318
-1.750 -0.2575 0.02189 0.01624 0.0199 1.0000 0.9649
-1.500 -0.2218 0.02204 0.01631 0.0175 1.0000 0.9724
-1.250 -0.1811 0.02208 0.01629 0.0139 1.0000 0.9769
-1.000 -0.1488 0.02221 0.01635 0.0121 1.0000 0.9837
-0.750 -0.1092 0.02219 0.01629 0.0086 1.0000 0.9874
-0.500 -0.0734 0.02225 0.01632 0.0059 1.0000 0.9924
-0.250 -0.0366 0.02231 0.01636 0.0029 1.0000 0.9964
0.000 0.0000 0.02239 0.01643 0.0000 1.0000 1.0000
0.250 0.0365 0.02231 0.01636 -0.0029 0.9964 1.0000
0.500 0.0733 0.02225 0.01632 -0.0059 0.9924 1.0000
0.750 0.1091 0.02218 0.01628 -0.0086 0.9874 1.0000
1.000 0.1486 0.02221 0.01635 -0.0120 0.9838 1.0000
1.250 0.1811 0.02208 0.01628 -0.0139 0.9770 1.0000
1.500 0.2217 0.02203 0.01630 -0.0174 0.9724 1.0000
1.750 0.2573 0.02189 0.01623 -0.0198 0.9650 1.0000
2.000 0.4633 0.01763 0.01231 -0.0533 0.9318 0.9977
2.250 0.5221 0.01599 0.01082 -0.0586 0.9121 0.9974
2.500 0.5631 0.01482 0.00978 -0.0605 0.8819 0.9992
2.750 0.6067 0.01352 0.00808 -0.0614 0.7195 0.9997
3.000 0.5995 0.01660 0.00834 -0.0544 0.1903 1.0000
3.250 0.6123 0.01782 0.00894 -0.0520 0.0945 1.0000
3.500 0.6297 0.01835 0.00944 -0.0501 0.0816 1.0000
3.750 0.6465 0.01894 0.01001 -0.0482 0.0737 1.0000
4.000 0.6642 0.01942 0.01051 -0.0465 0.0674 1.0000
4.250 0.6805 0.02036 0.01142 -0.0445 0.0629 1.0000
4.500 0.6995 0.02081 0.01196 -0.0429 0.0583 1.0000
4.750 0.7184 0.02149 0.01263 -0.0414 0.0543 1.0000
5.000 0.7408 0.02316 0.01429 -0.0405 0.0508 1.0000
5.250 0.7610 0.02367 0.01499 -0.0390 0.0478 1.0000
5.500 0.7827 0.02464 0.01608 -0.0378 0.0449 1.0000
5.750 0.8048 0.02586 0.01742 -0.0367 0.0429 1.0000
6.000 0.8271 0.02762 0.01928 -0.0359 0.0409 1.0000
6.250 0.8466 0.03003 0.02205 -0.0343 0.0387 1.0000
6.500 0.8638 0.03183 0.02423 -0.0319 0.0379 1.0000
6.750 0.8786 0.03448 0.02728 -0.0292 0.0379 1.0000
7.000 0.8885 0.03805 0.03125 -0.0259 0.0387 1.0000
9.000 0.7493 0.05849 0.05486 0.0256 0.0589 1.0000
9.250 0.7195 0.06040 0.05683 0.0327 0.0590 1.0000
9.500 0.6891 0.06271 0.05921 0.0389 0.0592 1.0000
9.750 0.6592 0.06568 0.06224 0.0436 0.0596 1.0000
10.000 0.6295 0.06935 0.06596 0.0468 0.0601 1.0000
10.250 0.6017 0.07372 0.07037 0.0485 0.0608 1.0000
10.500 0.5753 0.07883 0.07549 0.0487 0.0613 1.0000
10.750 0.5530 0.08451 0.08118 0.0478 0.0619 1.0000
11.000 0.5317 0.09122 0.08788 0.0453 0.0622 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 16-012 (naca16012-il)