AG45c -03f (ag45c03-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG45c -03f (ag45c03-il) Reynolds number: 50,000 Max Cl/Cd: 29.72 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag45c03-il-50000.txt Download as CSV file: xf-ag45c03-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.5648 0.11145 0.10508 0.0243 1.0000 0.1862
-7.000 -0.5500 0.10647 0.10012 0.0255 1.0000 0.1946
-6.750 -0.5643 0.10537 0.09917 0.0202 1.0000 0.2011
-6.500 -0.5487 0.10052 0.09434 0.0221 1.0000 0.2139
-6.250 -0.5386 0.09643 0.09029 0.0226 1.0000 0.2257
-6.000 -0.5324 0.09283 0.08675 0.0220 1.0000 0.2378
-5.750 -0.5258 0.08926 0.08325 0.0209 1.0000 0.2518
-5.500 -0.5186 0.08575 0.07980 0.0197 1.0000 0.2676
-5.250 -0.5176 0.08290 0.07703 0.0142 1.0000 0.2870
-4.750 -0.4961 0.07553 0.06977 0.0152 1.0000 0.3300
-4.500 -0.4804 0.07156 0.06585 0.0190 1.0000 0.3514
-3.750 -0.3706 0.04771 0.04046 -0.0280 1.0000 0.1596
-3.500 -0.3382 0.04145 0.03370 -0.0307 1.0000 0.1271
-3.000 -0.2767 0.03330 0.02413 -0.0334 1.0000 0.1161
-2.750 -0.2470 0.03016 0.02044 -0.0336 1.0000 0.1164
-2.500 -0.2175 0.02723 0.01709 -0.0334 1.0000 0.1182
-2.250 -0.1891 0.02516 0.01474 -0.0330 1.0000 0.1306
-2.000 -0.1606 0.02298 0.01245 -0.0324 1.0000 0.1459
-1.750 -0.1336 0.02114 0.01077 -0.0317 1.0000 0.1799
-1.500 -0.1057 0.01906 0.00894 -0.0309 1.0000 0.2575
-1.250 -0.0766 0.01410 0.00716 -0.0271 1.0000 1.0000
-1.000 -0.0492 0.01405 0.00637 -0.0270 1.0000 1.0000
-0.750 -0.0234 0.01402 0.00590 -0.0269 1.0000 1.0000
-0.500 0.0015 0.01403 0.00558 -0.0267 1.0000 1.0000
-0.250 0.0255 0.01408 0.00536 -0.0266 1.0000 1.0000
0.000 0.0478 0.01420 0.00528 -0.0264 1.0000 1.0000
0.250 0.0680 0.01442 0.00534 -0.0261 1.0000 1.0000
0.500 0.0864 0.01478 0.00553 -0.0260 1.0000 1.0000
0.750 0.1053 0.01524 0.00581 -0.0262 1.0000 1.0000
1.000 0.1249 0.01579 0.00621 -0.0268 1.0000 1.0000
1.250 0.1446 0.01642 0.00672 -0.0276 1.0000 1.0000
1.500 0.2086 0.01707 0.00726 -0.0362 0.9745 1.0000
1.750 0.2781 0.01755 0.00767 -0.0450 0.9456 1.0000
2.000 0.3403 0.01787 0.00798 -0.0516 0.9169 1.0000
2.250 0.3881 0.01816 0.00828 -0.0549 0.8879 1.0000
2.500 0.4246 0.01851 0.00861 -0.0557 0.8593 1.0000
2.750 0.4537 0.01894 0.00901 -0.0549 0.8316 1.0000
3.000 0.4791 0.01945 0.00948 -0.0535 0.8046 1.0000
3.250 0.5028 0.02001 0.01005 -0.0517 0.7784 1.0000
3.500 0.5261 0.02063 0.01064 -0.0498 0.7527 1.0000
3.750 0.5486 0.02128 0.01126 -0.0477 0.7279 1.0000
4.000 0.5707 0.02203 0.01197 -0.0457 0.7026 1.0000
4.250 0.5929 0.02284 0.01289 -0.0442 0.6748 1.0000
4.500 0.6152 0.02345 0.01351 -0.0422 0.6492 1.0000
4.750 0.6378 0.02398 0.01407 -0.0404 0.6228 1.0000
5.000 0.6607 0.02445 0.01459 -0.0386 0.5959 1.0000
5.250 0.6837 0.02487 0.01505 -0.0367 0.5688 1.0000
5.500 0.7069 0.02527 0.01553 -0.0348 0.5414 1.0000
5.750 0.7302 0.02566 0.01594 -0.0330 0.5133 1.0000
6.000 0.7537 0.02607 0.01636 -0.0311 0.4846 1.0000
6.250 0.7773 0.02655 0.01683 -0.0293 0.4554 1.0000
6.500 0.8009 0.02705 0.01735 -0.0276 0.4257 1.0000
6.750 0.8245 0.02774 0.01803 -0.0261 0.3955 1.0000
7.000 0.8478 0.02864 0.01901 -0.0248 0.3645 1.0000
7.250 0.8710 0.02959 0.01999 -0.0235 0.3345 1.0000
7.500 0.8941 0.03067 0.02110 -0.0223 0.3054 1.0000
7.750 0.9168 0.03202 0.02255 -0.0212 0.2779 1.0000
8.000 0.9389 0.03339 0.02398 -0.0201 0.2505 1.0000
8.250 0.9610 0.03519 0.02581 -0.0190 0.2264 1.0000
8.500 0.9829 0.03682 0.02738 -0.0179 0.2023 1.0000
8.750 1.0008 0.03981 0.03084 -0.0172 0.1826 1.0000
9.000 1.0204 0.04215 0.03328 -0.0163 0.1638 1.0000
9.250 1.0355 0.04592 0.03754 -0.0156 0.1510 1.0000
9.500 1.0487 0.04929 0.04124 -0.0151 0.1377 1.0000
9.750 1.0580 0.05421 0.04654 -0.0148 0.1316 1.0000
10.000 1.0534 0.06077 0.05375 -0.0158 0.1294 1.0000
10.250 1.0408 0.06784 0.06126 -0.0178 0.1292 1.0000
10.500 1.0224 0.07533 0.06900 -0.0209 0.1308 1.0000
10.750 1.0045 0.08258 0.07635 -0.0243 0.1325 1.0000
11.000 0.9899 0.08970 0.08348 -0.0279 0.1336 1.0000
11.250 0.8950 0.11871 0.11200 -0.0566 0.1898 1.0000
11.500 0.9005 0.12425 0.11758 -0.0570 0.1884 1.0000
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Polar data table (+)
Polar graphs
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