AG45c -03f (ag45c03-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG45c -03f (ag45c03-il) Reynolds number: 500,000 Max Cl/Cd: 78.09 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag45c03-il-500000-n5.txt Download as CSV file: xf-ag45c03-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG45c -03f
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.4670 0.08495 0.08294 0.0121 1.0000 0.0069
-7.250 -0.4692 0.08024 0.07825 0.0106 1.0000 0.0066
-7.000 -0.4727 0.07527 0.07330 0.0089 1.0000 0.0063
-6.000 -0.5424 0.06053 0.05839 -0.0104 1.0000 0.0052
-5.750 -0.5249 0.05200 0.04971 -0.0184 1.0000 0.0051
-5.500 -0.5059 0.04091 0.03829 -0.0255 1.0000 0.0051
-5.250 -0.4910 0.02342 0.01949 -0.0304 1.0000 0.0054
-5.000 -0.4669 0.02040 0.01604 -0.0308 1.0000 0.0056
-4.750 -0.4413 0.01862 0.01397 -0.0309 1.0000 0.0058
-4.500 -0.4151 0.01708 0.01216 -0.0308 1.0000 0.0060
-4.250 -0.3885 0.01610 0.01101 -0.0307 1.0000 0.0065
-4.000 -0.3593 0.01514 0.00986 -0.0311 0.9857 0.0071
-3.750 -0.3243 0.01406 0.00827 -0.0322 0.8408 0.0074
-3.500 -0.3011 0.01330 0.00701 -0.0309 0.7625 0.0075
-3.250 -0.2746 0.01251 0.00595 -0.0305 0.7400 0.0076
-3.000 -0.2476 0.01185 0.00509 -0.0302 0.7267 0.0078
-2.750 -0.2202 0.01131 0.00440 -0.0299 0.7165 0.0081
-2.500 -0.1927 0.01069 0.00362 -0.0297 0.7085 0.0087
-2.250 -0.1650 0.01032 0.00316 -0.0296 0.7013 0.0098
-2.000 -0.1369 0.01002 0.00279 -0.0295 0.6924 0.0114
-1.750 -0.1088 0.00970 0.00242 -0.0294 0.6833 0.0142
-1.500 -0.0807 0.00944 0.00215 -0.0293 0.6738 0.0213
-1.250 -0.0527 0.00919 0.00191 -0.0292 0.6634 0.0360
-1.000 -0.0248 0.00890 0.00172 -0.0292 0.6516 0.0673
-0.750 0.0032 0.00864 0.00157 -0.0292 0.6390 0.1095
-0.500 0.0310 0.00837 0.00143 -0.0292 0.6253 0.1648
-0.250 0.0588 0.00814 0.00132 -0.0292 0.6107 0.2263
0.000 0.0865 0.00788 0.00123 -0.0292 0.5953 0.3004
0.250 0.1140 0.00755 0.00116 -0.0292 0.5794 0.4055
0.500 0.1412 0.00716 0.00111 -0.0292 0.5633 0.5380
0.750 0.1674 0.00675 0.00109 -0.0289 0.5471 0.6782
1.000 0.1912 0.00639 0.00110 -0.0277 0.5313 0.8108
1.250 0.2131 0.00615 0.00109 -0.0258 0.5157 0.9308
1.500 0.2490 0.00620 0.00104 -0.0274 0.4977 1.0000
2.000 0.3050 0.00642 0.00105 -0.0272 0.4649 1.0000
2.250 0.3330 0.00653 0.00108 -0.0272 0.4482 1.0000
2.500 0.3610 0.00666 0.00111 -0.0271 0.4309 1.0000
2.750 0.3889 0.00679 0.00116 -0.0271 0.4134 1.0000
3.000 0.4168 0.00694 0.00121 -0.0271 0.3956 1.0000
3.250 0.4447 0.00708 0.00129 -0.0270 0.3772 1.0000
3.500 0.4725 0.00725 0.00137 -0.0270 0.3580 1.0000
3.750 0.5002 0.00743 0.00147 -0.0270 0.3390 1.0000
4.000 0.5280 0.00761 0.00157 -0.0269 0.3198 1.0000
4.250 0.5556 0.00782 0.00172 -0.0269 0.2999 1.0000
4.500 0.5833 0.00802 0.00186 -0.0269 0.2811 1.0000
4.750 0.6108 0.00825 0.00201 -0.0269 0.2607 1.0000
5.000 0.6383 0.00849 0.00218 -0.0269 0.2414 1.0000
5.250 0.6657 0.00875 0.00239 -0.0268 0.2211 1.0000
5.750 0.7202 0.00930 0.00283 -0.0268 0.1833 1.0000
6.000 0.7473 0.00961 0.00307 -0.0267 0.1650 1.0000
6.250 0.7742 0.00994 0.00336 -0.0267 0.1471 1.0000
6.500 0.8012 0.01026 0.00364 -0.0267 0.1315 1.0000
6.750 0.8280 0.01061 0.00395 -0.0266 0.1158 1.0000
7.000 0.8548 0.01097 0.00428 -0.0266 0.1018 1.0000
7.250 0.8813 0.01136 0.00464 -0.0265 0.0878 1.0000
7.500 0.9077 0.01176 0.00503 -0.0264 0.0754 1.0000
7.750 0.9339 0.01220 0.00544 -0.0263 0.0631 1.0000
8.000 0.9600 0.01266 0.00588 -0.0262 0.0521 1.0000
8.250 0.9858 0.01315 0.00636 -0.0261 0.0423 1.0000
8.500 1.0114 0.01368 0.00691 -0.0260 0.0341 1.0000
8.750 1.0368 0.01423 0.00746 -0.0258 0.0271 1.0000
9.000 1.0622 0.01476 0.00804 -0.0257 0.0224 1.0000
9.250 1.0869 0.01543 0.00873 -0.0254 0.0179 1.0000
9.500 1.1119 0.01598 0.00936 -0.0252 0.0155 1.0000
9.750 1.1360 0.01670 0.01011 -0.0250 0.0127 1.0000
10.000 1.1601 0.01742 0.01093 -0.0247 0.0111 1.0000
10.250 1.1839 0.01812 0.01176 -0.0244 0.0099 1.0000
10.500 1.2070 0.01894 0.01266 -0.0241 0.0088 1.0000
10.750 1.2282 0.02011 0.01395 -0.0237 0.0077 1.0000
11.000 1.2509 0.02089 0.01485 -0.0233 0.0071 1.0000
11.250 1.2728 0.02175 0.01583 -0.0230 0.0064 1.0000
11.500 1.2939 0.02270 0.01689 -0.0226 0.0059 1.0000
11.750 1.3136 0.02383 0.01814 -0.0221 0.0054 1.0000
12.000 1.3300 0.02540 0.01988 -0.0215 0.0050 1.0000
12.250 1.3454 0.02698 0.02164 -0.0208 0.0047 1.0000
12.500 1.3609 0.02842 0.02326 -0.0202 0.0045 1.0000
12.750 1.3739 0.03004 0.02506 -0.0194 0.0043 1.0000
13.000 1.3842 0.03186 0.02706 -0.0187 0.0041 1.0000
13.250 1.3909 0.03389 0.02927 -0.0179 0.0040 1.0000
13.500 1.3906 0.03621 0.03176 -0.0170 0.0038 1.0000
13.750 1.3874 0.03944 0.03518 -0.0180 0.0037 1.0000
14.000 1.3834 0.04372 0.03965 -0.0209 0.0037 1.0000
14.250 1.3771 0.04853 0.04462 -0.0240 0.0036 1.0000
14.500 1.3671 0.05414 0.05041 -0.0275 0.0035 1.0000
14.750 1.3540 0.06040 0.05682 -0.0312 0.0035 1.0000
15.000 1.3372 0.06735 0.06393 -0.0352 0.0035 1.0000
15.250 1.3175 0.07489 0.07163 -0.0393 0.0035 1.0000
15.500 1.2955 0.08297 0.07985 -0.0435 0.0035 1.0000
15.750 1.2718 0.09143 0.08845 -0.0477 0.0036 1.0000
16.000 1.2478 0.10014 0.09728 -0.0520 0.0036 1.0000
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Polar data table (+)
Polar graphs
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