NASA SC(2)-1006 AIRFOIL (sc21006-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NASA SC(2)-1006 AIRFOIL (sc21006-il) Reynolds number: 50,000 Max Cl/Cd: 28.31 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc21006-il-50000.txt Download as CSV file: xf-sc21006-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-1006 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4974 0.09686 0.08995 -0.0089 0.9999 0.2713
-9.750 -0.5045 0.09472 0.08793 -0.0074 0.9999 0.2820
-9.500 -0.5118 0.09275 0.08608 -0.0062 0.9999 0.2943
-9.000 -0.4990 0.08636 0.07976 -0.0025 0.9999 0.3260
-8.750 -0.5020 0.08433 0.07782 -0.0014 0.9999 0.3473
-8.500 -0.4914 0.08088 0.07439 0.0016 0.9999 0.3693
-8.250 -0.4944 0.07868 0.07229 0.0028 0.9999 0.3923
-8.000 -0.4832 0.07526 0.06888 0.0055 0.9999 0.4114
-7.750 -0.3774 0.04469 0.03658 -0.0718 0.9999 0.1368
-7.500 -0.3248 0.03783 0.02863 -0.0809 0.9999 0.1239
-7.250 -0.2840 0.03341 0.02359 -0.0849 0.9999 0.1205
-7.000 -0.2440 0.03000 0.01947 -0.0878 0.9999 0.1220
-6.750 -0.2098 0.02760 0.01668 -0.0894 0.9999 0.1345
-6.500 -0.1770 0.02535 0.01413 -0.0900 0.9999 0.1451
-6.250 -0.1468 0.02353 0.01221 -0.0900 0.9999 0.1692
-6.000 -0.1127 0.02140 0.01044 -0.0909 0.9999 0.2295
-5.750 -0.0849 0.01941 0.01070 -0.0885 0.9999 0.6135
-5.500 -0.0845 0.01991 0.01135 -0.0797 0.9999 0.7019
-5.250 -0.0854 0.02006 0.01146 -0.0710 0.9999 0.7629
-5.000 -0.0843 0.01975 0.01109 -0.0634 0.9999 0.8184
-4.750 -0.0828 0.01897 0.01024 -0.0565 0.9999 0.8754
-4.500 -0.0814 0.01755 0.00878 -0.0502 0.9999 0.9457
-4.250 -0.0512 0.01679 0.00778 -0.0523 0.9999 1.0001
-4.000 -0.0031 0.01683 0.00740 -0.0586 0.9999 1.0001
-3.750 0.0402 0.01693 0.00714 -0.0634 0.9999 1.0001
-3.500 0.0802 0.01706 0.00701 -0.0672 0.9999 1.0001
-3.250 0.1176 0.01723 0.00698 -0.0703 0.9999 1.0001
-3.000 0.1531 0.01741 0.00699 -0.0728 0.9999 1.0001
-2.750 0.1871 0.01762 0.00708 -0.0749 0.9999 1.0001
-2.500 0.2198 0.01784 0.00723 -0.0766 0.9999 1.0001
-2.250 0.2516 0.01809 0.00743 -0.0781 0.9999 1.0001
-2.000 0.2825 0.01835 0.00770 -0.0794 0.9999 1.0001
-1.750 0.3126 0.01863 0.00801 -0.0804 0.9999 1.0001
-1.500 0.3421 0.01894 0.00836 -0.0813 0.9999 1.0001
-1.250 0.3710 0.01927 0.00878 -0.0821 0.9999 1.0001
-1.000 0.3994 0.01962 0.00929 -0.0828 0.9999 1.0001
-0.750 0.4273 0.02000 0.00983 -0.0834 0.9999 1.0001
-0.500 0.4548 0.02040 0.01043 -0.0839 0.9999 1.0001
-0.250 0.4818 0.02085 0.01110 -0.0843 0.9999 1.0001
0.000 0.5084 0.02133 0.01185 -0.0847 0.9999 1.0001
0.250 0.5346 0.02185 0.01275 -0.0850 0.9999 1.0001
0.500 0.5603 0.02243 0.01370 -0.0852 0.9999 1.0001
0.750 0.5856 0.02306 0.01480 -0.0854 0.9999 1.0001
1.000 0.7408 0.02617 0.01452 -0.0965 0.1389 1.0001
1.250 0.7811 0.02841 0.01686 -0.0975 0.1188 1.0001
1.500 0.8197 0.03146 0.01989 -0.0984 0.1123 1.0001
1.750 0.8536 0.03433 0.02319 -0.0981 0.1104 1.0001
2.000 0.8834 0.03705 0.02650 -0.0972 0.1069 1.0001
2.250 0.9115 0.04031 0.03036 -0.0962 0.1063 1.0001
2.500 0.9380 0.04442 0.03488 -0.0953 0.1104 1.0001
2.750 0.9628 0.04852 0.03992 -0.0934 0.1218 1.0001
3.000 0.9871 0.05386 0.04582 -0.0921 0.1382 1.0001
4.750 0.9441 0.10539 0.10042 -0.1297 0.4284 1.0001
5.000 0.9468 0.10913 0.10413 -0.1271 0.3974 1.0001
|
Polar data table (+)
Polar graphs
<< Back to NASA SC(2)-1006 AIRFOIL (sc21006-il)