S8025 (8%) (s8025-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S8025 (8%) (s8025-il) Reynolds number: 200,000 Max Cl/Cd: 46.78 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8025-il-200000.txt Download as CSV file: xf-s8025-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5715 0.12405 0.12081 0.0220 1.0000 0.0471
-10.750 -0.5740 0.11920 0.11597 0.0193 1.0000 0.0473
-7.750 -0.7426 0.04384 0.03942 -0.0134 1.0000 0.0244
-7.500 -0.7461 0.03438 0.02886 -0.0126 1.0000 0.0204
-7.250 -0.7278 0.03127 0.02515 -0.0115 1.0000 0.0195
-7.000 -0.7079 0.02860 0.02209 -0.0106 1.0000 0.0193
-6.750 -0.6877 0.02550 0.01859 -0.0097 1.0000 0.0194
-6.500 -0.6663 0.02259 0.01536 -0.0087 1.0000 0.0198
-6.250 -0.6436 0.02093 0.01361 -0.0082 1.0000 0.0219
-6.000 -0.6190 0.01981 0.01237 -0.0075 1.0000 0.0244
-5.750 -0.5945 0.01835 0.01075 -0.0066 1.0000 0.0260
-5.500 -0.5721 0.01644 0.00876 -0.0055 1.0000 0.0286
-5.250 -0.5478 0.01533 0.00761 -0.0046 1.0000 0.0351
-5.000 -0.5250 0.01379 0.00623 -0.0037 1.0000 0.0658
-4.750 -0.5001 0.01304 0.00562 -0.0032 1.0000 0.1077
-4.500 -0.4747 0.01251 0.00518 -0.0028 1.0000 0.1410
-4.250 -0.4498 0.01191 0.00474 -0.0024 1.0000 0.1771
-4.000 -0.4249 0.01133 0.00433 -0.0019 1.0000 0.2195
-3.750 -0.3999 0.01079 0.00396 -0.0014 1.0000 0.2674
-3.500 -0.3752 0.01027 0.00364 -0.0008 1.0000 0.3213
-3.250 -0.3507 0.00980 0.00339 -0.0002 1.0000 0.3815
-3.000 -0.3265 0.00936 0.00319 0.0006 1.0000 0.4428
-2.750 -0.3026 0.00896 0.00305 0.0015 1.0000 0.5093
-2.500 -0.2793 0.00860 0.00293 0.0026 1.0000 0.5770
-2.250 -0.2561 0.00830 0.00285 0.0039 1.0000 0.6391
-2.000 -0.2334 0.00802 0.00279 0.0054 1.0000 0.6938
-1.750 -0.2113 0.00778 0.00275 0.0070 1.0000 0.7470
-1.500 -0.1901 0.00756 0.00272 0.0090 1.0000 0.8015
-1.250 -0.1683 0.00740 0.00273 0.0109 1.0000 0.8589
-1.000 -0.1340 0.00735 0.00277 0.0104 1.0000 0.9193
-0.750 -0.0795 0.00737 0.00277 0.0053 1.0000 0.9651
-0.500 -0.0227 0.00738 0.00274 -0.0007 1.0000 0.9936
-0.250 0.0119 0.00735 0.00269 -0.0026 0.9937 1.0000
0.000 0.0753 0.00736 0.00263 -0.0098 0.9282 1.0000
0.250 0.1162 0.00742 0.00250 -0.0118 0.8459 1.0000
0.500 0.1369 0.00761 0.00241 -0.0098 0.7816 1.0000
0.750 0.1578 0.00783 0.00237 -0.0080 0.7294 1.0000
1.000 0.1798 0.00807 0.00236 -0.0066 0.6833 1.0000
1.250 0.2027 0.00830 0.00237 -0.0053 0.6404 1.0000
1.500 0.2261 0.00852 0.00241 -0.0043 0.5989 1.0000
1.750 0.2501 0.00876 0.00245 -0.0033 0.5598 1.0000
2.000 0.2744 0.00901 0.00251 -0.0025 0.5239 1.0000
2.250 0.2993 0.00924 0.00261 -0.0018 0.4897 1.0000
2.500 0.3243 0.00950 0.00273 -0.0011 0.4578 1.0000
2.750 0.3495 0.00977 0.00287 -0.0005 0.4277 1.0000
3.000 0.3750 0.01004 0.00302 0.0000 0.3996 1.0000
3.250 0.4006 0.01032 0.00322 0.0005 0.3722 1.0000
3.500 0.4262 0.01061 0.00341 0.0010 0.3457 1.0000
3.750 0.4519 0.01092 0.00362 0.0015 0.3205 1.0000
4.000 0.4776 0.01124 0.00386 0.0019 0.2964 1.0000
4.250 0.5035 0.01156 0.00415 0.0023 0.2733 1.0000
4.500 0.5291 0.01194 0.00444 0.0027 0.2525 1.0000
4.750 0.5551 0.01228 0.00477 0.0031 0.2306 1.0000
5.000 0.5806 0.01271 0.00512 0.0035 0.2114 1.0000
5.250 0.6064 0.01312 0.00555 0.0039 0.1924 1.0000
5.500 0.6320 0.01356 0.00596 0.0043 0.1735 1.0000
5.750 0.6571 0.01409 0.00642 0.0047 0.1556 1.0000
6.000 0.6825 0.01459 0.00694 0.0051 0.1384 1.0000
6.250 0.7077 0.01514 0.00753 0.0055 0.1226 1.0000
6.500 0.7326 0.01576 0.00816 0.0059 0.1081 1.0000
6.750 0.7570 0.01652 0.00894 0.0064 0.0959 1.0000
7.000 0.7810 0.01739 0.00982 0.0070 0.0848 1.0000
7.250 0.8042 0.01841 0.01080 0.0075 0.0747 1.0000
7.500 0.8289 0.01915 0.01171 0.0081 0.0672 1.0000
7.750 0.8510 0.02072 0.01331 0.0088 0.0616 1.0000
8.000 0.8748 0.02173 0.01453 0.0094 0.0568 1.0000
8.250 0.8972 0.02294 0.01575 0.0100 0.0522 1.0000
8.500 0.9183 0.02504 0.01811 0.0108 0.0492 1.0000
8.750 0.9402 0.02640 0.01975 0.0115 0.0458 1.0000
9.000 0.9617 0.02737 0.02079 0.0120 0.0420 1.0000
9.250 0.9775 0.03021 0.02394 0.0127 0.0387 1.0000
9.500 0.9970 0.03125 0.02529 0.0134 0.0350 1.0000
9.750 1.0162 0.03211 0.02618 0.0139 0.0316 1.0000
10.000 1.0229 0.03610 0.03054 0.0148 0.0292 1.0000
10.250 1.0308 0.03897 0.03389 0.0158 0.0275 1.0000
10.500 1.0325 0.04242 0.03775 0.0166 0.0261 1.0000
10.750 1.0287 0.04604 0.04169 0.0173 0.0252 1.0000
11.000 1.0159 0.04979 0.04571 0.0179 0.0248 1.0000
11.250 0.9971 0.05392 0.05004 0.0169 0.0247 1.0000
11.500 0.9631 0.06221 0.05862 0.0099 0.0259 1.0000
11.750 0.9320 0.07235 0.06894 0.0009 0.0268 1.0000
12.000 0.8994 0.08396 0.08063 -0.0081 0.0283 1.0000
12.250 0.8689 0.09530 0.09198 -0.0153 0.0295 1.0000
12.500 0.7820 0.12674 0.12328 -0.0306 0.0395 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S8025 (8%) (s8025-il)