AG455ct -02f rot. (ag455ct02r-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG455ct -02f rot. (ag455ct02r-il) Reynolds number: 500,000 Max Cl/Cd: 75.23 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag455ct02r-il-500000-n5.txt Download as CSV file: xf-ag455ct02r-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5827 0.10284 0.10065 0.0223 1.0000 0.0092
-8.500 -0.5791 0.09877 0.09660 0.0202 1.0000 0.0092
-8.250 -0.5757 0.09466 0.09250 0.0180 1.0000 0.0092
-7.750 -0.4737 0.07335 0.07134 0.0055 1.0000 0.0083
-7.500 -0.4764 0.06888 0.06689 0.0038 1.0000 0.0078
-7.250 -0.4808 0.06399 0.06203 0.0012 1.0000 0.0074
-7.000 -0.4925 0.05176 0.04979 -0.0099 1.0000 0.0060
-6.500 -0.5152 0.05240 0.05006 -0.0205 1.0000 0.0057
-6.250 -0.4955 0.04480 0.04224 -0.0257 1.0000 0.0055
-6.000 -0.4747 0.03631 0.03338 -0.0295 1.0000 0.0054
-5.750 -0.4549 0.02496 0.02120 -0.0317 1.0000 0.0052
-5.500 -0.4316 0.01884 0.01419 -0.0318 1.0000 0.0054
-5.250 -0.4059 0.01652 0.01142 -0.0315 1.0000 0.0057
-5.000 -0.3799 0.01476 0.00931 -0.0312 1.0000 0.0060
-4.750 -0.3539 0.01344 0.00778 -0.0309 1.0000 0.0064
-4.500 -0.3274 0.01269 0.00693 -0.0307 1.0000 0.0067
-4.250 -0.3008 0.01212 0.00629 -0.0304 1.0000 0.0073
-4.000 -0.2742 0.01165 0.00576 -0.0301 1.0000 0.0081
-3.750 -0.2476 0.01102 0.00505 -0.0298 1.0000 0.0086
-3.500 -0.2133 0.01029 0.00420 -0.0311 0.9843 0.0089
-3.250 -0.1758 0.00964 0.00345 -0.0330 0.9513 0.0094
-3.000 -0.1432 0.00917 0.00280 -0.0337 0.8766 0.0109
-2.750 -0.1198 0.00916 0.00244 -0.0322 0.7932 0.0127
-2.500 -0.0937 0.00904 0.00210 -0.0316 0.7514 0.0165
-2.250 -0.0668 0.00889 0.00186 -0.0313 0.7288 0.0268
-2.000 -0.0395 0.00872 0.00167 -0.0311 0.7133 0.0481
-1.750 -0.0120 0.00851 0.00153 -0.0310 0.7009 0.0846
-1.500 0.0156 0.00825 0.00141 -0.0310 0.6868 0.1373
-1.250 0.0432 0.00798 0.00130 -0.0310 0.6717 0.2027
-1.000 0.0707 0.00771 0.00121 -0.0309 0.6550 0.2814
-0.750 0.0979 0.00738 0.00114 -0.0309 0.6367 0.3840
-0.500 0.1248 0.00698 0.00108 -0.0309 0.6170 0.5157
-0.250 0.1505 0.00653 0.00105 -0.0304 0.5963 0.6724
0.000 0.1736 0.00615 0.00106 -0.0291 0.5757 0.8153
0.500 0.2324 0.00600 0.00099 -0.0290 0.5290 1.0000
0.750 0.2601 0.00613 0.00099 -0.0288 0.5057 1.0000
1.250 0.3153 0.00642 0.00102 -0.0286 0.4578 1.0000
1.500 0.3429 0.00657 0.00105 -0.0285 0.4331 1.0000
1.750 0.3705 0.00674 0.00110 -0.0284 0.4090 1.0000
2.000 0.3981 0.00691 0.00116 -0.0283 0.3852 1.0000
2.250 0.4257 0.00709 0.00124 -0.0282 0.3619 1.0000
2.500 0.4533 0.00728 0.00134 -0.0281 0.3388 1.0000
2.750 0.4808 0.00748 0.00144 -0.0280 0.3163 1.0000
3.000 0.5083 0.00769 0.00156 -0.0279 0.2940 1.0000
3.500 0.5631 0.00813 0.00183 -0.0278 0.2509 1.0000
3.750 0.5904 0.00837 0.00201 -0.0277 0.2306 1.0000
4.000 0.6177 0.00862 0.00218 -0.0276 0.2099 1.0000
4.250 0.6449 0.00887 0.00238 -0.0275 0.1915 1.0000
4.500 0.6721 0.00915 0.00259 -0.0275 0.1722 1.0000
4.750 0.6992 0.00942 0.00283 -0.0274 0.1555 1.0000
5.000 0.7261 0.00974 0.00308 -0.0273 0.1375 1.0000
5.250 0.7530 0.01005 0.00335 -0.0272 0.1227 1.0000
5.500 0.7798 0.01038 0.00364 -0.0270 0.1077 1.0000
5.750 0.8065 0.01072 0.00396 -0.0269 0.0947 1.0000
6.000 0.8331 0.01108 0.00430 -0.0268 0.0816 1.0000
6.250 0.8595 0.01146 0.00465 -0.0266 0.0698 1.0000
6.750 0.9120 0.01228 0.00547 -0.0263 0.0489 1.0000
7.000 0.9380 0.01272 0.00591 -0.0261 0.0404 1.0000
7.250 0.9638 0.01319 0.00639 -0.0259 0.0333 1.0000
7.500 0.9893 0.01373 0.00693 -0.0257 0.0267 1.0000
7.750 1.0149 0.01421 0.00746 -0.0255 0.0223 1.0000
8.000 1.0398 0.01486 0.00812 -0.0252 0.0178 1.0000
8.250 1.0651 0.01537 0.00875 -0.0249 0.0157 1.0000
8.500 1.0897 0.01602 0.00945 -0.0246 0.0133 1.0000
8.750 1.1138 0.01677 0.01029 -0.0243 0.0113 1.0000
9.000 1.1381 0.01740 0.01102 -0.0239 0.0100 1.0000
9.250 1.1617 0.01816 0.01186 -0.0236 0.0089 1.0000
9.500 1.1839 0.01917 0.01298 -0.0231 0.0079 1.0000
9.750 1.2057 0.02021 0.01417 -0.0226 0.0073 1.0000
10.000 1.2279 0.02111 0.01524 -0.0221 0.0067 1.0000
10.250 1.2496 0.02202 0.01628 -0.0216 0.0061 1.0000
10.500 1.2710 0.02293 0.01730 -0.0211 0.0056 1.0000
10.750 1.2907 0.02407 0.01855 -0.0206 0.0051 1.0000
11.000 1.3053 0.02596 0.02063 -0.0197 0.0047 1.0000
11.250 1.3225 0.02730 0.02215 -0.0190 0.0045 1.0000
11.500 1.3379 0.02881 0.02385 -0.0182 0.0043 1.0000
11.750 1.3508 0.03053 0.02577 -0.0173 0.0041 1.0000
12.000 1.3612 0.03240 0.02784 -0.0164 0.0039 1.0000
12.250 1.3682 0.03448 0.03015 -0.0154 0.0038 1.0000
12.500 1.3694 0.03673 0.03259 -0.0142 0.0036 1.0000
12.750 1.3649 0.03956 0.03561 -0.0137 0.0036 1.0000
13.000 1.3578 0.04368 0.03993 -0.0158 0.0035 1.0000
13.250 1.3485 0.04910 0.04555 -0.0197 0.0035 1.0000
13.500 1.3361 0.05557 0.05221 -0.0244 0.0034 1.0000
13.750 1.3187 0.06325 0.06009 -0.0297 0.0034 1.0000
14.000 1.2972 0.07181 0.06881 -0.0351 0.0035 1.0000
14.250 1.2718 0.08105 0.07821 -0.0404 0.0035 1.0000
14.500 1.2450 0.09056 0.08785 -0.0455 0.0036 1.0000
14.750 1.2176 0.10026 0.09767 -0.0504 0.0037 1.0000
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Polar data table (+)
Polar graphs
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