NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 66-209 (naca66209-il) Reynolds number: 100,000 Max Cl/Cd: 32.4 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66209-il-100000.txt Download as CSV file: xf-naca66209-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5092 0.09819 0.09320 -0.0325 1.0000 0.0874
-9.250 -0.5246 0.09416 0.08928 -0.0382 1.0000 0.0893
-9.000 -0.5429 0.09013 0.08533 -0.0429 1.0000 0.0897
-8.750 -0.5232 0.08583 0.08105 -0.0388 1.0000 0.0941
-8.500 -0.5258 0.08246 0.07773 -0.0395 1.0000 0.0971
-8.250 -0.5417 0.07916 0.07449 -0.0403 1.0000 0.0994
-8.000 -0.5599 0.07622 0.07157 -0.0404 1.0000 0.1015
-7.750 -0.5892 0.07458 0.06981 -0.0393 1.0000 0.1034
-7.500 -0.6158 0.07421 0.06914 -0.0360 1.0000 0.1041
-7.250 -0.5877 0.06769 0.06306 -0.0344 1.0000 0.1103
-7.000 -0.6056 0.06614 0.06131 -0.0318 1.0000 0.1166
-6.750 -0.6111 0.06263 0.05778 -0.0294 1.0000 0.1203
-6.500 -0.6152 0.06133 0.05628 -0.0268 1.0000 0.1309
-6.250 -0.6097 0.05756 0.05269 -0.0244 1.0000 0.1384
-6.000 -0.6094 0.05510 0.05016 -0.0222 1.0000 0.1529
-4.250 -0.4990 0.03140 0.02331 -0.0127 1.0000 0.0853
-4.000 -0.4735 0.02951 0.02058 -0.0108 1.0000 0.0773
-3.750 -0.4493 0.02732 0.01815 -0.0098 1.0000 0.0752
-3.500 -0.4247 0.02522 0.01581 -0.0089 1.0000 0.0728
-3.250 -0.4001 0.02361 0.01396 -0.0078 1.0000 0.0721
-3.000 -0.3764 0.02237 0.01251 -0.0067 1.0000 0.0731
-2.750 -0.3536 0.02129 0.01133 -0.0057 1.0000 0.0783
-2.500 -0.3317 0.02019 0.01032 -0.0047 1.0000 0.0826
-2.250 -0.3101 0.01939 0.00950 -0.0035 1.0000 0.0882
-2.000 -0.2891 0.01858 0.00873 -0.0025 1.0000 0.0976
-1.750 -0.1198 0.01768 0.01077 -0.0187 1.0000 1.0000
-1.500 -0.1160 0.01756 0.01053 -0.0155 1.0000 1.0000
-1.250 -0.1122 0.01743 0.01030 -0.0124 1.0000 1.0000
-1.000 -0.1085 0.01729 0.01004 -0.0092 1.0000 1.0000
-0.750 -0.1048 0.01714 0.00980 -0.0059 1.0000 1.0000
-0.500 -0.1012 0.01697 0.00955 -0.0027 1.0000 1.0000
-0.250 -0.0971 0.01680 0.00931 0.0005 1.0000 1.0000
0.000 -0.0914 0.01665 0.00909 0.0034 1.0000 1.0000
0.250 -0.0827 0.01657 0.00893 0.0058 1.0000 1.0000
0.500 -0.0691 0.01660 0.00888 0.0074 1.0000 1.0000
0.750 -0.0522 0.01672 0.00892 0.0083 1.0000 1.0000
1.000 -0.0282 0.01700 0.00914 0.0079 0.9984 1.0000
1.250 0.0089 0.01760 0.00969 0.0049 0.9927 1.0000
1.500 0.0446 0.01815 0.01022 0.0022 0.9863 1.0000
1.750 0.0811 0.01876 0.01084 -0.0006 0.9799 1.0000
2.000 0.1168 0.01932 0.01142 -0.0031 0.9726 1.0000
2.250 0.1516 0.01988 0.01202 -0.0055 0.9647 1.0000
2.500 0.1922 0.02054 0.01279 -0.0089 0.9567 1.0000
2.750 0.2247 0.02098 0.01332 -0.0106 0.9465 1.0000
3.000 0.2618 0.02151 0.01397 -0.0131 0.9360 1.0000
3.250 0.3032 0.02204 0.01466 -0.0163 0.9250 1.0000
3.500 0.3465 0.02236 0.01523 -0.0194 0.9099 1.0000
3.750 0.5478 0.01691 0.00712 -0.0313 0.1239 1.0000
4.000 0.5563 0.01789 0.00799 -0.0277 0.1013 1.0000
4.250 0.5655 0.01880 0.00886 -0.0243 0.0888 1.0000
4.500 0.5761 0.01992 0.00987 -0.0213 0.0802 1.0000
4.750 0.5951 0.02102 0.01100 -0.0195 0.0755 1.0000
5.000 0.6199 0.02252 0.01249 -0.0186 0.0716 1.0000
5.250 0.6510 0.02504 0.01490 -0.0191 0.0682 1.0000
5.500 0.6761 0.02632 0.01647 -0.0181 0.0649 1.0000
5.750 0.7040 0.02855 0.01898 -0.0175 0.0648 1.0000
6.000 0.7303 0.03135 0.02207 -0.0168 0.0662 1.0000
6.250 0.7566 0.03426 0.02524 -0.0160 0.0690 1.0000
6.500 0.7784 0.03812 0.02985 -0.0136 0.0797 1.0000
8.000 0.8309 0.06571 0.06092 -0.0020 0.1708 1.0000
8.250 0.8306 0.06929 0.06455 -0.0007 0.1588 1.0000
8.500 0.7682 0.06563 0.06127 0.0038 0.1621 1.0000
8.750 0.7299 0.06952 0.06529 0.0054 0.1611 1.0000
9.000 0.8282 0.08112 0.07647 0.0020 0.1342 1.0000
9.250 0.7943 0.08426 0.07971 0.0026 0.1329 1.0000
9.500 0.7651 0.08900 0.08448 0.0000 0.1310 1.0000
9.750 0.7476 0.09461 0.09007 -0.0041 0.1277 1.0000
10.000 0.6741 0.09448 0.09024 0.0024 0.1350 1.0000
10.250 0.6377 0.10176 0.09746 -0.0045 0.1343 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 66-209 (naca66209-il)