AG455ct -02f rot. (ag455ct02r-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG455ct -02f rot. (ag455ct02r-il) Reynolds number: 100,000 Max Cl/Cd: 44.68 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag455ct02r-il-100000.txt Download as CSV file: xf-ag455ct02r-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG455ct -02f rot.
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5542 0.09758 0.09294 0.0154 1.0000 0.0762
-7.500 -0.5536 0.09412 0.08955 0.0105 1.0000 0.0795
-7.250 -0.5474 0.08948 0.08490 -0.0074 1.0000 0.0814
-7.000 -0.5397 0.08504 0.08055 0.0024 1.0000 0.0844
-6.750 -0.5285 0.08160 0.07712 0.0016 1.0000 0.0901
-6.500 -0.5123 0.07557 0.07086 -0.0168 1.0000 0.0956
-6.250 -0.5041 0.07243 0.06794 -0.0076 1.0000 0.1001
-6.000 -0.4842 0.06696 0.06222 -0.0194 1.0000 0.1098
-5.750 -0.4722 0.06359 0.05900 -0.0154 1.0000 0.1137
-5.500 -0.4131 0.04585 0.04162 -0.0177 1.0000 0.1277
-5.250 -0.3990 0.04081 0.03645 -0.0217 1.0000 0.1392
-5.000 -0.3829 0.03653 0.03205 -0.0239 1.0000 0.1525
-4.750 -0.3660 0.03273 0.02817 -0.0249 1.0000 0.1665
-4.500 -0.3486 0.02928 0.02465 -0.0252 1.0000 0.1812
-4.250 -0.3303 0.02610 0.02144 -0.0252 1.0000 0.1970
-4.000 -0.3102 0.02314 0.01840 -0.0255 1.0000 0.2162
-3.750 -0.2572 0.02488 0.01656 -0.0326 1.0000 0.0557
-3.500 -0.2314 0.02249 0.01408 -0.0325 1.0000 0.0597
-3.250 -0.2035 0.02058 0.01186 -0.0319 1.0000 0.0628
-3.000 -0.1753 0.01874 0.00971 -0.0311 1.0000 0.0655
-2.750 -0.1485 0.01708 0.00803 -0.0305 1.0000 0.0742
-2.500 -0.1220 0.01567 0.00668 -0.0298 1.0000 0.0900
-2.250 -0.0961 0.01422 0.00546 -0.0291 1.0000 0.1322
-2.000 -0.0745 0.01135 0.00455 -0.0284 1.0000 0.4937
-1.750 -0.0433 0.00989 0.00420 -0.0265 1.0000 1.0000
-1.500 -0.0176 0.00987 0.00387 -0.0261 1.0000 1.0000
-1.250 0.0078 0.00987 0.00362 -0.0257 1.0000 1.0000
-1.000 0.0329 0.00989 0.00347 -0.0254 1.0000 1.0000
-0.750 0.0577 0.00995 0.00338 -0.0251 1.0000 1.0000
-0.500 0.0819 0.01005 0.00338 -0.0249 1.0000 1.0000
-0.250 0.1049 0.01023 0.00347 -0.0248 1.0000 1.0000
0.000 0.1267 0.01055 0.00373 -0.0250 0.9998 1.0000
0.250 0.1891 0.01070 0.00379 -0.0324 0.9735 1.0000
0.500 0.2441 0.01076 0.00377 -0.0378 0.9439 1.0000
0.750 0.2884 0.01079 0.00374 -0.0406 0.9090 1.0000
1.000 0.3222 0.01088 0.00372 -0.0409 0.8726 1.0000
1.250 0.3488 0.01104 0.00376 -0.0397 0.8367 1.0000
1.500 0.3734 0.01127 0.00385 -0.0381 0.8035 1.0000
1.750 0.3975 0.01156 0.00397 -0.0366 0.7725 1.0000
2.000 0.4216 0.01189 0.00417 -0.0352 0.7417 1.0000
2.250 0.4458 0.01226 0.00440 -0.0339 0.7122 1.0000
2.500 0.4704 0.01262 0.00470 -0.0327 0.6820 1.0000
2.750 0.4952 0.01289 0.00489 -0.0317 0.6523 1.0000
3.000 0.5202 0.01312 0.00502 -0.0306 0.6226 1.0000
3.250 0.5453 0.01334 0.00517 -0.0296 0.5911 1.0000
3.500 0.5705 0.01360 0.00534 -0.0287 0.5585 1.0000
3.750 0.5956 0.01390 0.00557 -0.0278 0.5259 1.0000
4.000 0.6208 0.01424 0.00582 -0.0269 0.4918 1.0000
4.250 0.6460 0.01463 0.00611 -0.0262 0.4572 1.0000
4.500 0.6711 0.01509 0.00644 -0.0255 0.4229 1.0000
4.750 0.6961 0.01558 0.00689 -0.0248 0.3878 1.0000
5.000 0.7210 0.01615 0.00734 -0.0242 0.3544 1.0000
5.250 0.7460 0.01676 0.00789 -0.0236 0.3202 1.0000
5.500 0.7707 0.01745 0.00848 -0.0230 0.2887 1.0000
5.750 0.7952 0.01823 0.00919 -0.0225 0.2591 1.0000
6.250 0.8439 0.01997 0.01084 -0.0215 0.2044 1.0000
6.500 0.8680 0.02091 0.01181 -0.0209 0.1791 1.0000
6.750 0.8918 0.02210 0.01303 -0.0204 0.1571 1.0000
7.000 0.9150 0.02326 0.01414 -0.0198 0.1364 1.0000
7.250 0.9384 0.02481 0.01582 -0.0191 0.1187 1.0000
7.500 0.9610 0.02622 0.01737 -0.0185 0.1018 1.0000
7.750 0.9836 0.02822 0.01952 -0.0177 0.0896 1.0000
8.000 1.0051 0.03014 0.02159 -0.0170 0.0782 1.0000
8.250 1.0264 0.03295 0.02439 -0.0164 0.0706 1.0000
8.500 1.0456 0.03516 0.02721 -0.0154 0.0634 1.0000
8.750 1.0631 0.03881 0.03095 -0.0149 0.0583 1.0000
9.000 1.0753 0.04270 0.03565 -0.0136 0.0563 1.0000
9.250 1.0822 0.04730 0.04096 -0.0127 0.0542 1.0000
9.500 1.0866 0.05146 0.04561 -0.0121 0.0516 1.0000
9.750 1.0984 0.05408 0.04828 -0.0116 0.0485 1.0000
10.000 1.0916 0.05956 0.05424 -0.0114 0.0485 1.0000
10.250 1.0491 0.06826 0.06360 -0.0138 0.0513 1.0000
10.500 1.0155 0.07654 0.07209 -0.0194 0.0543 1.0000
10.750 0.9937 0.08479 0.08040 -0.0258 0.0561 1.0000
11.000 0.7813 0.10398 0.09958 -0.0316 0.0799 1.0000
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Polar data table (+)
Polar graphs
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