AG45ct -02f (ag45ct02r-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG45ct -02f (ag45ct02r-il) Reynolds number: 50,000 Max Cl/Cd: 30.34 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag45ct02r-il-50000.txt Download as CSV file: xf-ag45ct02r-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5841 0.12050 0.11399 0.0207 1.0000 0.1762
-8.500 -0.5584 0.11376 0.10722 0.0238 1.0000 0.1857
-8.250 -0.5766 0.11325 0.10686 0.0185 1.0000 0.1903
-8.000 -0.5526 0.10710 0.10063 0.0215 1.0000 0.2014
-7.750 -0.5483 0.10332 0.09693 0.0207 1.0000 0.2086
-7.500 -0.5575 0.10161 0.09533 0.0170 1.0000 0.2181
-7.250 -0.5431 0.09700 0.09074 0.0185 1.0000 0.2304
-7.000 -0.5363 0.09335 0.08716 0.0184 1.0000 0.2436
-6.750 -0.5327 0.09011 0.08398 0.0166 1.0000 0.2591
-6.500 -0.5315 0.08700 0.08096 0.0131 1.0000 0.2755
-6.250 -0.5138 0.08265 0.07664 0.0177 1.0000 0.2957
-5.750 -0.4968 0.07589 0.06999 0.0181 1.0000 0.3415
-5.500 -0.4866 0.07243 0.06659 0.0194 1.0000 0.3671
-5.250 -0.4786 0.06941 0.06364 0.0205 1.0000 0.4003
-5.000 -0.4676 0.06606 0.06032 0.0236 1.0000 0.4345
-4.750 -0.4026 0.05154 0.04475 -0.0237 1.0000 0.2189
-4.500 -0.3572 0.04159 0.03373 -0.0317 1.0000 0.1288
-4.250 -0.3273 0.03686 0.02831 -0.0332 1.0000 0.1158
-4.000 -0.2994 0.03324 0.02414 -0.0336 1.0000 0.1133
-3.750 -0.2711 0.03036 0.02067 -0.0336 1.0000 0.1169
-3.500 -0.2418 0.02765 0.01737 -0.0332 1.0000 0.1193
-3.250 -0.2142 0.02518 0.01473 -0.0326 1.0000 0.1262
-3.000 -0.1867 0.02329 0.01265 -0.0319 1.0000 0.1449
-2.750 -0.1590 0.02134 0.01069 -0.0310 1.0000 0.1732
-2.500 -0.1319 0.01926 0.00895 -0.0301 1.0000 0.2435
-2.250 -0.0959 0.01425 0.00703 -0.0272 1.0000 1.0000
-2.000 -0.0703 0.01418 0.00629 -0.0269 1.0000 1.0000
-1.750 -0.0457 0.01413 0.00580 -0.0265 1.0000 1.0000
-1.500 -0.0214 0.01412 0.00543 -0.0260 1.0000 1.0000
-1.250 0.0024 0.01413 0.00514 -0.0256 1.0000 1.0000
-1.000 0.0257 0.01417 0.00496 -0.0251 1.0000 1.0000
-0.750 0.0484 0.01426 0.00486 -0.0247 1.0000 1.0000
-0.500 0.0704 0.01440 0.00485 -0.0243 1.0000 1.0000
-0.250 0.0912 0.01462 0.00494 -0.0239 1.0000 1.0000
0.000 0.1111 0.01492 0.00511 -0.0236 1.0000 1.0000
0.250 0.1308 0.01533 0.00540 -0.0235 1.0000 1.0000
0.500 0.1505 0.01582 0.00581 -0.0237 1.0000 1.0000
0.750 0.1700 0.01640 0.00632 -0.0242 1.0000 1.0000
1.000 0.1893 0.01709 0.00694 -0.0249 1.0000 1.0000
1.250 0.2488 0.01788 0.00773 -0.0329 0.9778 1.0000
1.500 0.3233 0.01844 0.00835 -0.0426 0.9447 1.0000
1.750 0.3942 0.01870 0.00873 -0.0505 0.9124 1.0000
2.000 0.4418 0.01891 0.00903 -0.0534 0.8774 1.0000
2.250 0.4799 0.01911 0.00928 -0.0537 0.8441 1.0000
2.500 0.5078 0.01945 0.00966 -0.0522 0.8107 1.0000
2.750 0.5319 0.01987 0.01007 -0.0500 0.7777 1.0000
3.000 0.5551 0.02033 0.01051 -0.0475 0.7460 1.0000
3.250 0.5772 0.02088 0.01102 -0.0449 0.7147 1.0000
3.500 0.5988 0.02155 0.01175 -0.0428 0.6811 1.0000
3.750 0.6208 0.02206 0.01225 -0.0404 0.6499 1.0000
4.000 0.6430 0.02255 0.01275 -0.0383 0.6176 1.0000
4.250 0.6655 0.02298 0.01320 -0.0362 0.5854 1.0000
4.500 0.6884 0.02337 0.01357 -0.0341 0.5539 1.0000
4.750 0.7115 0.02377 0.01395 -0.0319 0.5227 1.0000
5.000 0.7345 0.02440 0.01462 -0.0303 0.4881 1.0000
5.250 0.7577 0.02500 0.01516 -0.0284 0.4551 1.0000
5.500 0.7809 0.02574 0.01586 -0.0268 0.4219 1.0000
5.750 0.8039 0.02663 0.01682 -0.0253 0.3876 1.0000
6.000 0.8271 0.02754 0.01765 -0.0238 0.3556 1.0000
6.250 0.8499 0.02874 0.01887 -0.0225 0.3236 1.0000
6.500 0.8722 0.03005 0.02026 -0.0213 0.2921 1.0000
6.750 0.8944 0.03148 0.02173 -0.0201 0.2626 1.0000
7.000 0.9163 0.03322 0.02361 -0.0189 0.2355 1.0000
7.250 0.9371 0.03492 0.02539 -0.0178 0.2086 1.0000
7.500 0.9591 0.03707 0.02747 -0.0167 0.1873 1.0000
7.750 0.9766 0.03963 0.03046 -0.0156 0.1661 1.0000
8.000 0.9937 0.04324 0.03447 -0.0148 0.1528 1.0000
8.250 1.0092 0.04626 0.03776 -0.0139 0.1382 1.0000
8.500 1.0211 0.05068 0.04257 -0.0133 0.1305 1.0000
8.750 1.0228 0.05655 0.04911 -0.0134 0.1272 1.0000
9.000 1.0354 0.06007 0.05267 -0.0126 0.1190 1.0000
9.250 1.0251 0.06659 0.05972 -0.0137 0.1182 1.0000
9.500 1.0116 0.07324 0.06667 -0.0155 0.1186 1.0000
9.750 0.9971 0.07986 0.07346 -0.0178 0.1194 1.0000
10.000 0.9835 0.08625 0.07992 -0.0201 0.1201 1.0000
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Polar data table (+)
Polar graphs
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