AG47ct -02f rot. (ag47ct02r-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG47ct -02f rot. (ag47ct02r-il) Reynolds number: 50,000 Max Cl/Cd: 30.3 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag47ct02r-il-50000-n5.txt Download as CSV file: xf-ag47ct02r-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6297 0.12435 0.11743 0.0325 1.0000 0.0875
-9.000 -0.6335 0.12195 0.11518 0.0284 1.0000 0.0902
-8.750 -0.6377 0.11943 0.11275 0.0236 1.0000 0.0909
-8.500 -0.6189 0.11323 0.10647 0.0278 1.0000 0.0954
-8.250 -0.6141 0.10969 0.10297 0.0265 1.0000 0.0994
-8.000 -0.6175 0.10694 0.10032 0.0216 1.0000 0.1036
-7.750 -0.6196 0.10381 0.09727 0.0122 1.0000 0.1047
-7.500 -0.6059 0.09846 0.09195 0.0179 1.0000 0.1075
-7.250 -0.5968 0.09439 0.08791 0.0165 1.0000 0.1099
-6.750 -0.4970 0.07018 0.06399 -0.0005 1.0000 0.0571
-6.250 -0.5381 0.07017 0.06336 -0.0074 1.0000 0.0484
-6.000 -0.5223 0.06532 0.05843 -0.0102 1.0000 0.0461
-5.750 -0.5034 0.05999 0.05293 -0.0139 1.0000 0.0438
-5.500 -0.4812 0.05419 0.04682 -0.0179 1.0000 0.0414
-5.000 -0.4290 0.04400 0.03544 -0.0232 1.0000 0.0382
-4.750 -0.4046 0.03999 0.03099 -0.0241 1.0000 0.0382
-4.500 -0.3807 0.03621 0.02689 -0.0250 1.0000 0.0396
-4.250 -0.3562 0.03376 0.02419 -0.0253 1.0000 0.0432
-4.000 -0.3287 0.03091 0.02083 -0.0255 1.0000 0.0458
-3.750 -0.3004 0.02814 0.01752 -0.0253 1.0000 0.0473
-3.500 -0.2719 0.02576 0.01462 -0.0247 1.0000 0.0494
-3.250 -0.2453 0.02391 0.01261 -0.0244 1.0000 0.0560
-3.000 -0.2177 0.02232 0.01067 -0.0235 1.0000 0.0637
-2.750 -0.1912 0.02080 0.00909 -0.0228 1.0000 0.0743
-2.500 -0.1641 0.01951 0.00768 -0.0223 1.0000 0.0941
-2.250 -0.1372 0.01818 0.00650 -0.0221 1.0000 0.1365
-2.000 -0.1119 0.01616 0.00550 -0.0221 1.0000 0.3082
-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 0.2571 0.01427 0.00403 -0.0185 0.9838 1.0000
1.750 0.3087 0.01450 0.00439 -0.0233 0.9332 1.0000
2.000 0.3546 0.01469 0.00466 -0.0263 0.8756 1.0000
2.250 0.3912 0.01493 0.00487 -0.0269 0.8161 1.0000
2.500 0.4186 0.01526 0.00508 -0.0254 0.7602 1.0000
2.750 0.4421 0.01570 0.00541 -0.0234 0.7088 1.0000
3.000 0.4650 0.01612 0.00576 -0.0216 0.6530 1.0000
3.250 0.4876 0.01650 0.00605 -0.0198 0.5898 1.0000
3.500 0.5099 0.01696 0.00631 -0.0180 0.5190 1.0000
3.750 0.5324 0.01757 0.00663 -0.0165 0.4414 1.0000
4.000 0.5552 0.01836 0.00716 -0.0154 0.3634 1.0000
4.250 0.5788 0.01930 0.00781 -0.0147 0.2961 1.0000
4.500 0.6029 0.02033 0.00864 -0.0142 0.2437 1.0000
4.750 0.6281 0.02145 0.00963 -0.0140 0.2044 1.0000
5.000 0.6530 0.02258 0.01071 -0.0136 0.1728 1.0000
5.250 0.6777 0.02383 0.01204 -0.0131 0.1511 1.0000
5.500 0.7021 0.02505 0.01331 -0.0126 0.1306 1.0000
5.750 0.7264 0.02647 0.01480 -0.0120 0.1159 1.0000
6.000 0.7509 0.02804 0.01654 -0.0114 0.1032 1.0000
6.250 0.7747 0.02956 0.01826 -0.0109 0.0903 1.0000
6.500 0.7991 0.03187 0.02097 -0.0102 0.0831 1.0000
6.750 0.8217 0.03379 0.02296 -0.0098 0.0751 1.0000
7.000 0.8442 0.03632 0.02613 -0.0093 0.0669 1.0000
7.250 0.8653 0.03901 0.02904 -0.0089 0.0630 1.0000
7.500 0.8835 0.04322 0.03396 -0.0086 0.0600 1.0000
7.750 0.8983 0.04743 0.03887 -0.0087 0.0555 1.0000
8.000 0.9144 0.04988 0.04149 -0.0086 0.0512 1.0000
8.250 0.9245 0.05445 0.04640 -0.0089 0.0496 1.0000
8.500 0.9264 0.06057 0.05314 -0.0103 0.0491 1.0000
8.750 0.9230 0.06692 0.05992 -0.0125 0.0489 1.0000
9.000 0.9152 0.07337 0.06664 -0.0155 0.0489 1.0000
9.250 0.9046 0.07990 0.07333 -0.0195 0.0490 1.0000
9.500 0.8922 0.08654 0.08000 -0.0245 0.0493 1.0000
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Polar data table (+)
Polar graphs
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