NACA 0010-66 (naca001066-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0010-66 (naca001066-il) Reynolds number: 50,000 Max Cl/Cd: 20.85 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001066-il-50000.txt Download as CSV file: xf-naca001066-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-66
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6101 0.11012 0.10276 0.0016 1.0000 0.3497
-9.000 -0.5997 0.10672 0.09933 0.0037 1.0000 0.3695
-8.750 -0.6087 0.10422 0.09689 0.0062 1.0000 0.3910
-8.500 -0.6018 0.10074 0.09343 0.0086 1.0000 0.4127
-8.250 -0.5959 0.09763 0.09032 0.0110 1.0000 0.4344
-7.750 -0.5891 0.09138 0.08411 0.0161 1.0000 0.4796
-7.000 -0.8258 0.06666 0.05890 0.0112 1.0000 0.1900
-6.750 -0.8405 0.06053 0.05192 0.0161 1.0000 0.1624
-6.500 -0.8316 0.05645 0.04766 0.0187 1.0000 0.1582
-6.250 -0.8269 0.05281 0.04362 0.0223 1.0000 0.1558
-6.000 -0.8206 0.04930 0.03961 0.0260 1.0000 0.1536
-5.750 -0.8131 0.04590 0.03541 0.0302 1.0000 0.1497
-5.500 -0.7992 0.04321 0.03205 0.0334 1.0000 0.1484
-5.250 -0.7792 0.04032 0.02900 0.0348 1.0000 0.1508
-5.000 -0.7588 0.03827 0.02675 0.0364 1.0000 0.1565
-4.750 -0.7364 0.03614 0.02411 0.0380 1.0000 0.1606
-4.500 -0.7097 0.03404 0.02157 0.0389 1.0000 0.1647
-4.250 -0.2881 0.02961 0.01998 -0.0299 1.0000 1.0000
-4.000 -0.2728 0.02922 0.01918 -0.0281 1.0000 1.0000
-3.750 -0.2570 0.02890 0.01853 -0.0264 1.0000 1.0000
-3.500 -0.2409 0.02862 0.01796 -0.0246 1.0000 1.0000
-3.250 -0.2246 0.02837 0.01747 -0.0228 1.0000 1.0000
-3.000 -0.2080 0.02816 0.01704 -0.0210 1.0000 1.0000
-2.750 -0.1912 0.02797 0.01666 -0.0192 1.0000 1.0000
-2.500 -0.1742 0.02780 0.01633 -0.0175 1.0000 1.0000
-2.250 -0.1571 0.02766 0.01602 -0.0157 1.0000 1.0000
-2.000 -0.1400 0.02753 0.01576 -0.0140 1.0000 1.0000
-1.750 -0.1226 0.02742 0.01554 -0.0122 1.0000 1.0000
-1.500 -0.1053 0.02733 0.01535 -0.0105 1.0000 1.0000
-1.250 -0.0878 0.02725 0.01518 -0.0087 1.0000 1.0000
-1.000 -0.0703 0.02719 0.01506 -0.0070 1.0000 1.0000
-0.750 -0.0528 0.02714 0.01496 -0.0052 1.0000 1.0000
-0.500 -0.0352 0.02711 0.01489 -0.0035 1.0000 1.0000
-0.250 -0.0176 0.02709 0.01484 -0.0017 1.0000 1.0000
0.000 0.0000 0.02708 0.01483 0.0000 1.0000 1.0000
0.250 0.0176 0.02709 0.01484 0.0017 1.0000 1.0000
0.500 0.0352 0.02711 0.01489 0.0035 1.0000 1.0000
0.750 0.0528 0.02714 0.01495 0.0052 1.0000 1.0000
1.000 0.0703 0.02719 0.01505 0.0070 1.0000 1.0000
1.250 0.0878 0.02725 0.01518 0.0087 1.0000 1.0000
1.500 0.1053 0.02732 0.01534 0.0105 1.0000 1.0000
1.750 0.1227 0.02742 0.01553 0.0122 1.0000 1.0000
2.000 0.1400 0.02752 0.01575 0.0140 1.0000 1.0000
2.250 0.1572 0.02765 0.01601 0.0157 1.0000 1.0000
2.500 0.1743 0.02779 0.01632 0.0175 1.0000 1.0000
2.750 0.1912 0.02796 0.01665 0.0192 1.0000 1.0000
3.000 0.2080 0.02814 0.01702 0.0210 1.0000 1.0000
3.250 0.2246 0.02836 0.01745 0.0228 1.0000 1.0000
3.500 0.2410 0.02860 0.01794 0.0246 1.0000 1.0000
3.750 0.2571 0.02888 0.01851 0.0264 1.0000 1.0000
4.000 0.2729 0.02920 0.01916 0.0281 1.0000 1.0000
4.250 0.2882 0.02958 0.01995 0.0299 1.0000 1.0000
4.500 0.7096 0.03403 0.02157 -0.0389 0.1647 1.0000
4.750 0.7363 0.03613 0.02411 -0.0380 0.1606 1.0000
5.000 0.7587 0.03826 0.02674 -0.0364 0.1565 1.0000
5.250 0.7791 0.04031 0.02899 -0.0348 0.1508 1.0000
5.500 0.7991 0.04320 0.03204 -0.0334 0.1484 1.0000
5.750 0.8130 0.04589 0.03540 -0.0302 0.1497 1.0000
6.000 0.8206 0.04929 0.03960 -0.0260 0.1536 1.0000
6.250 0.8269 0.05280 0.04361 -0.0223 0.1558 1.0000
6.500 0.8315 0.05645 0.04768 -0.0187 0.1582 1.0000
6.750 0.8405 0.06052 0.05191 -0.0161 0.1624 1.0000
7.000 0.7570 0.05640 0.04929 -0.0052 0.1890 1.0000
8.750 0.6082 0.10414 0.09681 -0.0062 0.3908 1.0000
9.000 0.6003 0.10669 0.09930 -0.0037 0.3694 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0010-66 (naca001066-il)