NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 64-208 (naca64208-il) Reynolds number: 50,000 Max Cl/Cd: 26.62 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64208-il-50000.txt Download as CSV file: xf-naca64208-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-208
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5358 0.10799 0.10110 0.0041 1.0000 0.2718
-8.750 -0.5358 0.10514 0.09826 0.0039 1.0000 0.2876
-8.500 -0.5441 0.10299 0.09620 0.0033 1.0000 0.3032
-8.250 -0.5186 0.09796 0.09115 0.0055 1.0000 0.3271
-8.000 -0.5150 0.09482 0.08806 0.0062 1.0000 0.3481
-7.750 -0.5190 0.09287 0.08620 0.0073 1.0000 0.3726
-7.500 -0.4903 0.08843 0.08171 0.0100 1.0000 0.4101
-7.250 -0.4924 0.08660 0.07997 0.0120 1.0000 0.4416
-7.000 -0.4669 0.08218 0.07551 0.0136 1.0000 0.4734
-5.750 -0.5153 0.04825 0.04067 -0.0358 1.0000 0.1677
-5.500 -0.4929 0.04354 0.03535 -0.0368 1.0000 0.1453
-5.250 -0.4705 0.03977 0.03087 -0.0369 1.0000 0.1343
-5.000 -0.4475 0.03619 0.02673 -0.0364 1.0000 0.1263
-4.750 -0.4226 0.03340 0.02334 -0.0355 1.0000 0.1207
-4.500 -0.3982 0.03069 0.02026 -0.0346 1.0000 0.1186
-4.250 -0.3731 0.02841 0.01759 -0.0335 1.0000 0.1189
-4.000 -0.3490 0.02646 0.01537 -0.0323 1.0000 0.1259
-3.750 -0.3249 0.02474 0.01350 -0.0309 1.0000 0.1335
-3.500 -0.3012 0.02309 0.01182 -0.0291 1.0000 0.1412
-3.250 -0.2794 0.02168 0.01046 -0.0274 1.0000 0.1591
-3.000 -0.0997 0.01827 0.00927 -0.0356 1.0000 1.0000
-2.750 -0.0887 0.01782 0.00864 -0.0344 1.0000 1.0000
-2.500 -0.0797 0.01742 0.00810 -0.0327 1.0000 1.0000
-2.250 -0.0737 0.01707 0.00766 -0.0305 1.0000 1.0000
-2.000 -0.0713 0.01678 0.00731 -0.0277 1.0000 1.0000
-1.750 -0.0733 0.01653 0.00702 -0.0242 1.0000 1.0000
-1.500 -0.0795 0.01632 0.00677 -0.0199 1.0000 1.0000
-1.250 -0.0857 0.01615 0.00653 -0.0156 1.0000 1.0000
-1.000 -0.0832 0.01606 0.00627 -0.0127 1.0000 1.0000
-0.750 -0.0712 0.01608 0.00612 -0.0113 1.0000 1.0000
-0.500 -0.0547 0.01618 0.00605 -0.0107 1.0000 1.0000
-0.250 -0.0362 0.01634 0.00605 -0.0103 1.0000 1.0000
0.000 -0.0167 0.01655 0.00613 -0.0100 1.0000 1.0000
0.250 0.0032 0.01681 0.00626 -0.0098 1.0000 1.0000
0.500 0.0233 0.01711 0.00646 -0.0097 1.0000 1.0000
0.750 0.0435 0.01745 0.00672 -0.0096 1.0000 1.0000
1.000 0.0635 0.01784 0.00705 -0.0096 1.0000 1.0000
1.250 0.0836 0.01826 0.00744 -0.0096 1.0000 1.0000
1.500 0.1035 0.01873 0.00789 -0.0096 1.0000 1.0000
1.750 0.1234 0.01923 0.00839 -0.0096 1.0000 1.0000
2.000 0.1429 0.01978 0.00895 -0.0097 1.0000 1.0000
2.250 0.1624 0.02037 0.00957 -0.0098 1.0000 1.0000
2.500 0.1816 0.02101 0.01026 -0.0099 1.0000 1.0000
2.750 0.2007 0.02169 0.01104 -0.0101 1.0000 1.0000
3.000 0.2195 0.02242 0.01186 -0.0103 1.0000 1.0000
3.250 0.2472 0.02339 0.01296 -0.0123 0.9954 1.0000
3.500 0.2955 0.02478 0.01460 -0.0181 0.9799 1.0000
3.750 0.3421 0.02606 0.01624 -0.0233 0.9622 1.0000
4.000 0.3994 0.02743 0.01804 -0.0300 0.9409 1.0000
4.250 0.4612 0.02827 0.01946 -0.0362 0.9056 1.0000
4.500 0.5877 0.02208 0.01108 -0.0222 0.2009 1.0000
4.750 0.6073 0.02432 0.01295 -0.0206 0.1580 1.0000
5.000 0.6358 0.02651 0.01490 -0.0198 0.1382 1.0000
5.250 0.6668 0.02856 0.01707 -0.0193 0.1219 1.0000
5.500 0.6995 0.03099 0.01970 -0.0188 0.1159 1.0000
5.750 0.7298 0.03388 0.02278 -0.0184 0.1132 1.0000
6.000 0.7561 0.03699 0.02628 -0.0176 0.1102 1.0000
6.250 0.7795 0.03986 0.02975 -0.0165 0.1077 1.0000
6.500 0.8020 0.04361 0.03395 -0.0156 0.1095 1.0000
6.750 0.8214 0.04736 0.03850 -0.0142 0.1159 1.0000
7.000 0.8391 0.05232 0.04390 -0.0135 0.1237 1.0000
7.250 0.8559 0.05797 0.05006 -0.0130 0.1383 1.0000
7.500 0.8521 0.06439 0.05768 -0.0142 0.1712 1.0000
7.750 0.8347 0.07782 0.07181 -0.0251 0.2624 1.0000
8.000 0.7790 0.08609 0.08000 -0.0355 0.2868 1.0000
8.250 0.7043 0.07709 0.07132 -0.0206 0.2136 1.0000
8.500 0.7070 0.10317 0.09667 -0.0571 0.4153 1.0000
8.750 0.7105 0.10689 0.10042 -0.0568 0.3982 1.0000
9.000 0.5906 0.10517 0.09905 -0.0456 0.3773 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 64-208 (naca64208-il)