SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: SIKORSKY SSC-A09 AIRFOIL (ssca09-il) Reynolds number: 50,000 Max Cl/Cd: 27.94 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ssca09-il-50000-n5.txt Download as CSV file: xf-ssca09-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SIKORSKY SSC-A09 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5747 0.09917 0.09255 -0.0056 1.0000 0.0597
-8.750 -0.5752 0.09365 0.08707 -0.0095 1.0000 0.0561
-8.500 -0.5915 0.08572 0.07906 -0.0196 1.0000 0.0501
-8.250 -0.5875 0.08154 0.07489 -0.0204 1.0000 0.0489
-8.000 -0.5871 0.07705 0.07035 -0.0223 1.0000 0.0479
-7.750 -0.5864 0.07253 0.06573 -0.0241 1.0000 0.0472
-7.500 -0.5843 0.06809 0.06114 -0.0255 1.0000 0.0466
-7.250 -0.5800 0.06381 0.05666 -0.0264 1.0000 0.0463
-7.000 -0.5734 0.05973 0.05233 -0.0269 1.0000 0.0463
-6.750 -0.5647 0.05585 0.04817 -0.0270 1.0000 0.0463
-6.500 -0.5542 0.05218 0.04416 -0.0267 1.0000 0.0462
-6.250 -0.5421 0.04870 0.04032 -0.0260 1.0000 0.0459
-6.000 -0.5288 0.04541 0.03665 -0.0249 1.0000 0.0454
-5.750 -0.5143 0.04240 0.03324 -0.0236 1.0000 0.0450
-5.500 -0.4987 0.03966 0.03006 -0.0220 1.0000 0.0448
-5.250 -0.4819 0.03715 0.02715 -0.0204 1.0000 0.0449
-5.000 -0.4635 0.03485 0.02448 -0.0188 1.0000 0.0453
-4.750 -0.4438 0.03289 0.02215 -0.0173 1.0000 0.0470
-4.500 -0.4227 0.03120 0.02004 -0.0159 1.0000 0.0494
-4.250 -0.4006 0.02959 0.01811 -0.0145 1.0000 0.0512
-4.000 -0.3784 0.02781 0.01624 -0.0133 1.0000 0.0530
-3.750 -0.3559 0.02646 0.01481 -0.0120 1.0000 0.0554
-3.500 -0.3337 0.02541 0.01362 -0.0106 1.0000 0.0603
-3.250 -0.3119 0.02437 0.01247 -0.0093 1.0000 0.0661
-3.000 -0.2907 0.02340 0.01141 -0.0081 1.0000 0.0724
-2.750 -0.2699 0.02250 0.01042 -0.0070 1.0000 0.0841
-2.500 -0.2489 0.02155 0.00946 -0.0060 1.0000 0.1055
-2.250 -0.0904 0.01878 0.00976 -0.0208 1.0000 0.9958
-2.000 -0.0740 0.01857 0.00933 -0.0200 1.0000 1.0000
-1.750 -0.0717 0.01844 0.00905 -0.0166 1.0000 1.0000
-1.500 -0.0694 0.01832 0.00880 -0.0131 1.0000 1.0000
-1.250 -0.0663 0.01822 0.00857 -0.0097 1.0000 1.0000
-1.000 -0.0617 0.01814 0.00834 -0.0064 1.0000 1.0000
-0.750 -0.0552 0.01810 0.00816 -0.0035 1.0000 1.0000
-0.500 -0.0457 0.01810 0.00802 -0.0011 1.0000 1.0000
-0.250 -0.0328 0.01815 0.00794 0.0008 1.0000 1.0000
0.000 -0.0172 0.01826 0.00792 0.0021 1.0000 1.0000
0.250 0.0113 0.01849 0.00801 0.0010 0.9959 1.0000
0.500 0.0499 0.01882 0.00823 -0.0019 0.9880 1.0000
0.750 0.0900 0.01919 0.00852 -0.0051 0.9790 1.0000
1.000 0.1382 0.01959 0.00887 -0.0097 0.9660 1.0000
1.250 0.2025 0.01988 0.00918 -0.0167 0.9438 1.0000
1.500 0.2661 0.01992 0.00928 -0.0229 0.9178 1.0000
1.750 0.3074 0.01987 0.00929 -0.0249 0.8951 1.0000
2.000 0.3394 0.01978 0.00926 -0.0249 0.8722 1.0000
2.250 0.3705 0.01958 0.00915 -0.0245 0.8491 1.0000
2.500 0.3948 0.01941 0.00905 -0.0229 0.8230 1.0000
2.750 0.4185 0.01919 0.00891 -0.0211 0.7941 1.0000
3.000 0.4412 0.01897 0.00875 -0.0191 0.7590 1.0000
3.250 0.4621 0.01880 0.00869 -0.0169 0.7111 1.0000
3.500 0.4861 0.01852 0.00833 -0.0145 0.6421 1.0000
3.750 0.5092 0.01848 0.00781 -0.0115 0.5426 1.0000
4.000 0.5278 0.01916 0.00787 -0.0091 0.4499 1.0000
4.250 0.5469 0.02005 0.00835 -0.0076 0.3896 1.0000
4.500 0.5682 0.02093 0.00894 -0.0066 0.3517 1.0000
4.750 0.5910 0.02173 0.00960 -0.0060 0.3246 1.0000
5.000 0.6146 0.02253 0.01029 -0.0054 0.3033 1.0000
5.250 0.6393 0.02330 0.01109 -0.0050 0.2859 1.0000
5.500 0.6648 0.02408 0.01189 -0.0047 0.2718 1.0000
5.750 0.6906 0.02488 0.01273 -0.0044 0.2585 1.0000
6.000 0.7165 0.02572 0.01360 -0.0041 0.2464 1.0000
6.250 0.7423 0.02658 0.01460 -0.0038 0.2349 1.0000
6.500 0.7674 0.02747 0.01564 -0.0035 0.2223 1.0000
6.750 0.7920 0.02841 0.01673 -0.0032 0.2096 1.0000
7.000 0.8156 0.02934 0.01785 -0.0028 0.1962 1.0000
7.250 0.8387 0.03032 0.01899 -0.0024 0.1829 1.0000
7.500 0.8613 0.03137 0.02021 -0.0019 0.1696 1.0000
7.750 0.8830 0.03248 0.02150 -0.0014 0.1561 1.0000
8.000 0.9038 0.03365 0.02287 -0.0008 0.1424 1.0000
8.250 0.9238 0.03493 0.02438 -0.0001 0.1292 1.0000
8.500 0.9427 0.03622 0.02585 0.0006 0.1168 1.0000
8.750 0.9611 0.03748 0.02721 0.0013 0.1061 1.0000
9.000 0.9778 0.03935 0.02946 0.0022 0.0955 1.0000
9.250 0.9929 0.04140 0.03185 0.0031 0.0869 1.0000
9.500 1.0091 0.04284 0.03333 0.0040 0.0811 1.0000
9.750 1.0182 0.04601 0.03706 0.0051 0.0747 1.0000
10.000 1.0311 0.04746 0.03854 0.0060 0.0698 1.0000
10.250 1.0348 0.05118 0.04270 0.0072 0.0669 1.0000
10.500 1.0305 0.05549 0.04751 0.0083 0.0646 1.0000
10.750 1.0222 0.05958 0.05195 0.0094 0.0628 1.0000
11.000 1.0084 0.06355 0.05617 0.0103 0.0616 1.0000
11.250 0.9878 0.06861 0.06146 0.0099 0.0611 1.0000
11.500 0.9463 0.07769 0.07080 0.0057 0.0629 1.0000
11.750 0.9000 0.09059 0.08380 -0.0034 0.0652 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SIKORSKY SSC-A09 AIRFOIL (ssca09-il)