AG47ct -02f rot. (ag47ct02r-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG47ct -02f rot. (ag47ct02r-il) Reynolds number: 50,000 Max Cl/Cd: 30.55 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag47ct02r-il-50000.txt Download as CSV file: xf-ag47ct02r-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AG47ct -02f rot.
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6314 0.11451 0.10795 0.0293 1.0000 0.1734
-8.000 -0.6144 0.10893 0.10238 0.0313 1.0000 0.1825
-7.750 -0.6287 0.10794 0.10152 0.0250 1.0000 0.1877
-7.500 -0.6100 0.10231 0.09589 0.0283 1.0000 0.1991
-7.000 -0.6021 0.09495 0.08867 0.0243 1.0000 0.2179
-6.750 -0.5965 0.09140 0.08517 0.0215 1.0000 0.2310
-6.500 -0.5868 0.08740 0.08121 0.0213 1.0000 0.2456
-6.000 -0.5706 0.08047 0.07436 0.0172 1.0000 0.2857
-5.750 -0.5560 0.07615 0.07004 0.0219 1.0000 0.3054
-5.500 -0.5460 0.07264 0.06658 0.0228 1.0000 0.3333
-5.250 -0.5384 0.06954 0.06354 0.0230 1.0000 0.3704
-5.000 -0.5282 0.06629 0.06037 0.0285 1.0000 0.4137
-4.750 -0.5183 0.06335 0.05751 0.0364 1.0000 0.4716
-4.000 -0.3462 0.03728 0.02842 -0.0260 1.0000 0.1309
-3.750 -0.3132 0.03338 0.02367 -0.0267 1.0000 0.1182
-3.500 -0.2844 0.03000 0.01997 -0.0267 1.0000 0.1155
-3.250 -0.2538 0.02740 0.01673 -0.0264 1.0000 0.1180
-3.000 -0.2261 0.02502 0.01421 -0.0261 1.0000 0.1287
-2.750 -0.1967 0.02273 0.01162 -0.0253 1.0000 0.1376
-2.500 -0.1690 0.02089 0.00975 -0.0245 1.0000 0.1654
-2.250 -0.1405 0.01896 0.00789 -0.0235 1.0000 0.2162
-2.000 -0.1089 0.01364 0.00569 -0.0208 1.0000 1.0000
-1.750 -0.0818 0.01357 0.00491 -0.0203 1.0000 1.0000
-1.500 -0.0554 0.01352 0.00442 -0.0199 1.0000 1.0000
-1.250 -0.0293 0.01348 0.00400 -0.0195 1.0000 1.0000
-1.000 -0.0032 0.01346 0.00370 -0.0192 1.0000 1.0000
-0.750 0.0227 0.01345 0.00348 -0.0188 1.0000 1.0000
-0.500 0.0485 0.01345 0.00331 -0.0185 1.0000 1.0000
-0.250 0.0741 0.01347 0.00318 -0.0181 1.0000 1.0000
0.000 0.0996 0.01351 0.00312 -0.0178 1.0000 1.0000
0.250 0.1249 0.01356 0.00312 -0.0175 1.0000 1.0000
0.500 0.1499 0.01363 0.00317 -0.0171 1.0000 1.0000
0.750 0.1745 0.01373 0.00327 -0.0168 1.0000 1.0000
1.000 0.1987 0.01385 0.00344 -0.0166 1.0000 1.0000
1.250 0.2223 0.01403 0.00368 -0.0164 1.0000 1.0000
1.500 0.2452 0.01427 0.00402 -0.0163 1.0000 1.0000
1.750 0.2669 0.01460 0.00446 -0.0163 1.0000 1.0000
2.000 0.2878 0.01508 0.00506 -0.0166 1.0000 1.0000
2.250 0.3082 0.01571 0.00580 -0.0174 1.0000 1.0000
2.500 0.3390 0.01654 0.00679 -0.0207 0.9926 1.0000
2.750 0.4544 0.01672 0.00764 -0.0364 0.9131 1.0000
3.000 0.5002 0.01669 0.00780 -0.0363 0.8334 1.0000
3.250 0.5202 0.01703 0.00803 -0.0313 0.7585 1.0000
3.500 0.5359 0.01770 0.00846 -0.0262 0.6777 1.0000
3.750 0.5521 0.01824 0.00870 -0.0216 0.5845 1.0000
4.000 0.5702 0.01907 0.00906 -0.0179 0.4815 1.0000
4.250 0.5913 0.02036 0.00980 -0.0156 0.3921 1.0000
4.500 0.6150 0.02187 0.01096 -0.0143 0.3257 1.0000
4.750 0.6393 0.02347 0.01227 -0.0133 0.2790 1.0000
5.000 0.6651 0.02529 0.01413 -0.0125 0.2443 1.0000
5.250 0.6901 0.02709 0.01603 -0.0117 0.2152 1.0000
5.500 0.7156 0.02931 0.01829 -0.0111 0.1948 1.0000
5.750 0.7411 0.03185 0.02126 -0.0105 0.1778 1.0000
6.000 0.7650 0.03437 0.02412 -0.0100 0.1611 1.0000
6.250 0.7889 0.03785 0.02791 -0.0096 0.1533 1.0000
6.500 0.8104 0.04160 0.03234 -0.0094 0.1449 1.0000
6.750 0.8290 0.04574 0.03707 -0.0096 0.1365 1.0000
7.000 0.8448 0.05151 0.04351 -0.0106 0.1367 1.0000
7.250 0.8580 0.05771 0.05017 -0.0120 0.1392 1.0000
7.500 0.8730 0.06358 0.05621 -0.0126 0.1414 1.0000
8.000 0.8029 0.10142 0.09474 -0.0661 0.3462 1.0000
8.250 0.7978 0.10459 0.09785 -0.0662 0.3282 1.0000
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Polar data table (+)
Polar graphs
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