S8025 (8%) (s8025-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S8025 (8%) (s8025-il) Reynolds number: 50,000 Max Cl/Cd: 22.69 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8025-il-50000.txt Download as CSV file: xf-s8025-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S8025 (8%)
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6092 0.09684 0.09040 0.0316 1.0000 0.2896
-7.750 -0.6675 0.07915 0.07285 0.0037 1.0000 0.1336
-7.500 -0.6875 0.06801 0.06142 -0.0066 1.0000 0.1101
-7.250 -0.6831 0.06207 0.05533 -0.0084 1.0000 0.1062
-7.000 -0.6866 0.05386 0.04628 -0.0121 1.0000 0.0978
-6.750 -0.6752 0.04868 0.04058 -0.0126 1.0000 0.0979
-6.500 -0.6580 0.04490 0.03674 -0.0123 1.0000 0.1029
-6.250 -0.6403 0.04068 0.03203 -0.0120 1.0000 0.1065
-6.000 -0.6204 0.03643 0.02692 -0.0114 1.0000 0.1114
-5.750 -0.5984 0.03341 0.02357 -0.0106 1.0000 0.1253
-5.500 -0.5756 0.03073 0.02093 -0.0097 1.0000 0.1462
-5.250 -0.5525 0.02833 0.01841 -0.0086 1.0000 0.1771
-5.000 -0.5295 0.02632 0.01638 -0.0074 1.0000 0.2154
-4.750 -0.5062 0.02460 0.01472 -0.0061 1.0000 0.2572
-4.500 -0.4825 0.02302 0.01326 -0.0048 1.0000 0.3025
-4.250 -0.4589 0.02156 0.01196 -0.0034 1.0000 0.3552
-4.000 -0.4365 0.02034 0.01104 -0.0017 1.0000 0.4191
-3.750 -0.4154 0.01929 0.01030 0.0006 1.0000 0.4934
-3.500 -0.3962 0.01845 0.00985 0.0037 1.0000 0.5731
-3.250 -0.3787 0.01777 0.00949 0.0077 1.0000 0.6564
-3.000 -0.3630 0.01726 0.00923 0.0126 1.0000 0.7376
-2.750 -0.3440 0.01693 0.00905 0.0176 1.0000 0.8182
-2.500 -0.2857 0.01700 0.00883 0.0158 1.0000 0.9120
-2.250 -0.1271 0.01649 0.00739 -0.0083 1.0000 1.0000
-2.000 -0.1161 0.01579 0.00659 -0.0080 1.0000 1.0000
-1.750 -0.1033 0.01527 0.00599 -0.0072 1.0000 1.0000
-1.500 -0.0885 0.01490 0.00553 -0.0062 1.0000 1.0000
-1.250 -0.0721 0.01465 0.00517 -0.0052 1.0000 1.0000
-1.000 -0.0543 0.01449 0.00492 -0.0042 1.0000 1.0000
-0.750 -0.0354 0.01438 0.00474 -0.0031 1.0000 1.0000
-0.500 -0.0162 0.01433 0.00464 -0.0021 1.0000 1.0000
-0.250 0.0031 0.01431 0.00459 -0.0011 1.0000 1.0000
0.000 0.0221 0.01433 0.00461 0.0000 1.0000 1.0000
0.250 0.0403 0.01441 0.00471 0.0011 1.0000 1.0000
0.500 0.0567 0.01456 0.00491 0.0022 1.0000 1.0000
0.750 0.0693 0.01486 0.00526 0.0034 1.0000 1.0000
1.000 0.0771 0.01542 0.00583 0.0047 1.0000 1.0000
1.250 0.1192 0.01628 0.00678 -0.0013 0.9797 1.0000
1.500 0.2446 0.01654 0.00740 -0.0194 0.9095 1.0000
1.750 0.3000 0.01671 0.00760 -0.0225 0.8419 1.0000
2.000 0.3235 0.01716 0.00791 -0.0198 0.7859 1.0000
2.250 0.3429 0.01769 0.00828 -0.0165 0.7370 1.0000
2.500 0.3627 0.01827 0.00875 -0.0137 0.6916 1.0000
2.750 0.3835 0.01887 0.00921 -0.0112 0.6498 1.0000
3.000 0.4047 0.01947 0.00966 -0.0089 0.6111 1.0000
3.250 0.4271 0.02012 0.01024 -0.0072 0.5722 1.0000
3.500 0.4499 0.02079 0.01082 -0.0054 0.5372 1.0000
3.750 0.4733 0.02155 0.01154 -0.0040 0.5023 1.0000
4.000 0.4967 0.02232 0.01224 -0.0026 0.4704 1.0000
4.250 0.5203 0.02315 0.01303 -0.0013 0.4401 1.0000
4.500 0.5441 0.02407 0.01392 -0.0001 0.4110 1.0000
4.750 0.5678 0.02502 0.01485 0.0011 0.3824 1.0000
5.000 0.5916 0.02608 0.01596 0.0021 0.3550 1.0000
5.250 0.6152 0.02728 0.01725 0.0030 0.3288 1.0000
5.500 0.6385 0.02851 0.01857 0.0040 0.3036 1.0000
5.750 0.6623 0.02986 0.01991 0.0050 0.2823 1.0000
6.000 0.6846 0.03150 0.02180 0.0057 0.2589 1.0000
6.250 0.7078 0.03324 0.02362 0.0066 0.2408 1.0000
6.500 0.7292 0.03528 0.02587 0.0074 0.2223 1.0000
6.750 0.7492 0.03781 0.02879 0.0079 0.2063 1.0000
7.000 0.7683 0.04056 0.03184 0.0084 0.1927 1.0000
7.250 0.7861 0.04323 0.03477 0.0089 0.1789 1.0000
7.500 0.8009 0.04718 0.03911 0.0089 0.1713 1.0000
7.750 0.8091 0.05236 0.04472 0.0082 0.1663 1.0000
8.000 0.8051 0.05930 0.05217 0.0056 0.1640 1.0000
8.250 0.7960 0.06672 0.05985 0.0020 0.1643 1.0000
8.500 0.7844 0.07423 0.06747 -0.0023 0.1660 1.0000
8.750 0.7776 0.08099 0.07426 -0.0058 0.1677 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S8025 (8%) (s8025-il)