AG45ct -02f (ag45ct02r-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG45ct -02f (ag45ct02r-il) Reynolds number: 500,000 Max Cl/Cd: 76.07 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag45ct02r-il-500000-n5.txt Download as CSV file: xf-ag45ct02r-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG45ct -02f
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4680 0.07999 0.07796 0.0062 1.0000 0.0077
-8.000 -0.4710 0.07521 0.07319 0.0046 1.0000 0.0073
-7.750 -0.4762 0.06998 0.06799 0.0025 1.0000 0.0069
-7.250 -0.5610 0.06658 0.06448 -0.0077 1.0000 0.0058
-7.000 -0.5458 0.06054 0.05836 -0.0142 1.0000 0.0056
-6.750 -0.5305 0.05276 0.05044 -0.0213 1.0000 0.0055
-6.500 -0.5134 0.04423 0.04167 -0.0269 1.0000 0.0054
-6.250 -0.4966 0.03390 0.03085 -0.0307 1.0000 0.0053
-6.000 -0.4810 0.02228 0.01812 -0.0319 1.0000 0.0053
-5.750 -0.4575 0.01884 0.01409 -0.0317 1.0000 0.0056
-5.500 -0.4329 0.01656 0.01138 -0.0313 1.0000 0.0058
-5.250 -0.4079 0.01497 0.00954 -0.0310 1.0000 0.0062
-5.000 -0.3821 0.01407 0.00851 -0.0307 1.0000 0.0064
-4.750 -0.3560 0.01327 0.00759 -0.0303 1.0000 0.0068
-4.500 -0.3298 0.01275 0.00698 -0.0300 1.0000 0.0074
-4.250 -0.3036 0.01215 0.00630 -0.0296 1.0000 0.0080
-4.000 -0.2708 0.01134 0.00537 -0.0306 0.9878 0.0084
-3.750 -0.2347 0.01058 0.00450 -0.0323 0.9614 0.0086
-3.500 -0.1986 0.00994 0.00368 -0.0338 0.9068 0.0091
-3.250 -0.1744 0.00964 0.00307 -0.0326 0.8261 0.0101
-3.000 -0.1493 0.00952 0.00270 -0.0317 0.7738 0.0117
-2.750 -0.1227 0.00936 0.00234 -0.0312 0.7460 0.0141
-2.500 -0.0957 0.00918 0.00207 -0.0309 0.7284 0.0199
-2.250 -0.0684 0.00896 0.00184 -0.0307 0.7149 0.0362
-1.750 -0.0135 0.00848 0.00153 -0.0305 0.6924 0.1102
-1.500 0.0140 0.00820 0.00142 -0.0305 0.6797 0.1698
-1.250 0.0414 0.00791 0.00130 -0.0304 0.6660 0.2399
-1.000 0.0686 0.00760 0.00122 -0.0304 0.6512 0.3272
-0.750 0.0955 0.00727 0.00115 -0.0303 0.6353 0.4316
-0.500 0.1221 0.00694 0.00110 -0.0301 0.6176 0.5437
-0.250 0.1480 0.00661 0.00107 -0.0296 0.5986 0.6579
0.000 0.1719 0.00626 0.00106 -0.0285 0.5798 0.7819
0.250 0.1951 0.00594 0.00106 -0.0268 0.5598 0.9318
0.500 0.2346 0.00601 0.00101 -0.0293 0.5356 1.0000
0.750 0.2621 0.00613 0.00101 -0.0291 0.5131 1.0000
1.000 0.2895 0.00627 0.00101 -0.0289 0.4909 1.0000
1.250 0.3169 0.00641 0.00103 -0.0287 0.4681 1.0000
1.500 0.3443 0.00656 0.00107 -0.0286 0.4446 1.0000
1.750 0.3717 0.00672 0.00112 -0.0284 0.4218 1.0000
2.000 0.3991 0.00688 0.00118 -0.0283 0.3992 1.0000
2.250 0.4265 0.00705 0.00125 -0.0282 0.3773 1.0000
2.500 0.4538 0.00724 0.00135 -0.0280 0.3551 1.0000
2.750 0.4812 0.00742 0.00144 -0.0279 0.3339 1.0000
3.000 0.5085 0.00762 0.00155 -0.0278 0.3142 1.0000
3.250 0.5358 0.00782 0.00168 -0.0277 0.2944 1.0000
3.500 0.5631 0.00802 0.00183 -0.0276 0.2756 1.0000
3.750 0.5902 0.00825 0.00198 -0.0274 0.2556 1.0000
4.000 0.6174 0.00848 0.00215 -0.0273 0.2365 1.0000
4.250 0.6444 0.00874 0.00233 -0.0272 0.2158 1.0000
4.500 0.6714 0.00899 0.00255 -0.0271 0.1976 1.0000
4.750 0.6982 0.00928 0.00277 -0.0270 0.1771 1.0000
5.000 0.7250 0.00958 0.00301 -0.0268 0.1592 1.0000
5.250 0.7517 0.00990 0.00327 -0.0267 0.1407 1.0000
5.500 0.7782 0.01023 0.00357 -0.0265 0.1241 1.0000
5.750 0.8046 0.01060 0.00388 -0.0264 0.1078 1.0000
6.000 0.8310 0.01096 0.00421 -0.0262 0.0934 1.0000
6.250 0.8572 0.01134 0.00456 -0.0260 0.0798 1.0000
6.500 0.8833 0.01175 0.00494 -0.0259 0.0671 1.0000
6.750 0.9091 0.01219 0.00537 -0.0257 0.0549 1.0000
7.000 0.9348 0.01266 0.00582 -0.0254 0.0441 1.0000
7.250 0.9602 0.01316 0.00630 -0.0252 0.0349 1.0000
7.500 0.9857 0.01364 0.00680 -0.0250 0.0285 1.0000
7.750 1.0109 0.01416 0.00735 -0.0247 0.0229 1.0000
8.000 1.0357 0.01476 0.00799 -0.0244 0.0183 1.0000
8.250 1.0606 0.01532 0.00863 -0.0241 0.0157 1.0000
8.500 1.0850 0.01594 0.00930 -0.0237 0.0133 1.0000
8.750 1.1087 0.01670 0.01013 -0.0233 0.0111 1.0000
9.000 1.1328 0.01732 0.01085 -0.0229 0.0099 1.0000
9.250 1.1562 0.01805 0.01167 -0.0225 0.0088 1.0000
9.500 1.1784 0.01898 0.01268 -0.0220 0.0079 1.0000
9.750 1.1996 0.02006 0.01394 -0.0214 0.0072 1.0000
10.000 1.2215 0.02094 0.01495 -0.0209 0.0067 1.0000
10.250 1.2429 0.02185 0.01598 -0.0204 0.0062 1.0000
10.500 1.2639 0.02275 0.01699 -0.0199 0.0056 1.0000
10.750 1.2838 0.02378 0.01813 -0.0193 0.0051 1.0000
11.000 1.2998 0.02534 0.01984 -0.0185 0.0047 1.0000
11.250 1.3145 0.02697 0.02165 -0.0176 0.0045 1.0000
11.500 1.3296 0.02840 0.02326 -0.0167 0.0043 1.0000
11.750 1.3424 0.03000 0.02508 -0.0158 0.0042 1.0000
12.000 1.3524 0.03180 0.02707 -0.0147 0.0040 1.0000
12.250 1.3589 0.03378 0.02924 -0.0136 0.0039 1.0000
12.500 1.3589 0.03596 0.03160 -0.0122 0.0037 1.0000
12.750 1.3551 0.03881 0.03463 -0.0120 0.0037 1.0000
13.000 1.3500 0.04263 0.03865 -0.0137 0.0036 1.0000
13.250 1.3427 0.04740 0.04361 -0.0167 0.0035 1.0000
13.500 1.3328 0.05300 0.04939 -0.0203 0.0035 1.0000
13.750 1.3190 0.05958 0.05615 -0.0246 0.0035 1.0000
14.000 1.3022 0.06689 0.06363 -0.0292 0.0035 1.0000
14.250 1.2814 0.07501 0.07191 -0.0339 0.0035 1.0000
14.500 1.2588 0.08352 0.08057 -0.0386 0.0035 1.0000
14.750 1.2344 0.09241 0.08958 -0.0432 0.0036 1.0000
15.000 1.2097 0.10146 0.09876 -0.0478 0.0036 1.0000
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Polar data table (+)
Polar graphs
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