AG47ct -02f rot. (ag47ct02r-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG47ct -02f rot. (ag47ct02r-il) Reynolds number: 100,000 Max Cl/Cd: 41.86 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag47ct02r-il-100000.txt Download as CSV file: xf-ag47ct02r-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6310 0.11881 0.11395 0.0305 1.0000 0.0628
-8.750 -0.6338 0.11641 0.11165 0.0251 1.0000 0.0636
-8.500 -0.6358 0.11363 0.10894 0.0192 1.0000 0.0639
-8.250 -0.6270 0.10720 0.10250 0.0215 1.0000 0.0651
-8.000 -0.6134 0.10268 0.09796 0.0250 1.0000 0.0678
-7.750 -0.6076 0.09907 0.09439 0.0238 1.0000 0.0703
-7.500 -0.6036 0.09545 0.09081 0.0211 1.0000 0.0730
-7.250 -0.5972 0.09138 0.08677 0.0119 1.0000 0.0762
-7.000 -0.5833 0.08643 0.08166 -0.0051 1.0000 0.0777
-6.750 -0.5776 0.08157 0.07698 0.0043 1.0000 0.0798
-6.500 -0.5000 0.06490 0.06041 -0.0126 1.0000 0.0912
-6.250 -0.4902 0.06050 0.05622 -0.0044 1.0000 0.0940
-6.000 -0.4795 0.05635 0.05207 -0.0052 1.0000 0.0991
-5.750 -0.4677 0.04985 0.04538 -0.0139 1.0000 0.1061
-5.500 -0.4554 0.04629 0.04190 -0.0117 1.0000 0.1110
-5.250 -0.4398 0.04107 0.03652 -0.0158 1.0000 0.1214
-5.000 -0.4235 0.03691 0.03225 -0.0174 1.0000 0.1352
-4.750 -0.4071 0.03327 0.02858 -0.0177 1.0000 0.1509
-4.500 -0.4133 0.04500 0.03969 -0.0199 1.0000 0.1647
-4.250 -0.3902 0.04190 0.03643 -0.0213 1.0000 0.1903
-4.000 -0.3684 0.03903 0.03351 -0.0214 1.0000 0.2180
-3.750 -0.3215 0.03238 0.02587 -0.0262 1.0000 0.1496
-3.500 -0.2734 0.02429 0.01599 -0.0258 1.0000 0.0607
-3.250 -0.2446 0.02165 0.01291 -0.0252 1.0000 0.0593
-3.000 -0.2155 0.02023 0.01099 -0.0245 1.0000 0.0640
-2.750 -0.1884 0.01790 0.00860 -0.0241 1.0000 0.0696
-2.500 -0.1608 0.01634 0.00693 -0.0233 1.0000 0.0793
-2.250 -0.1344 0.01493 0.00568 -0.0227 1.0000 0.1001
-2.000 -0.1086 0.01340 0.00447 -0.0220 1.0000 0.1565
-1.750 -0.0800 0.00958 0.00363 -0.0205 1.0000 1.0000
-1.500 -0.0533 0.00954 0.00323 -0.0201 1.0000 1.0000
-1.250 -0.0269 0.00951 0.00291 -0.0197 1.0000 1.0000
-1.000 -0.0006 0.00950 0.00269 -0.0194 1.0000 1.0000
-0.750 0.0257 0.00949 0.00253 -0.0190 1.0000 1.0000
-0.500 0.0518 0.00950 0.00241 -0.0187 1.0000 1.0000
-0.250 0.0778 0.00952 0.00232 -0.0184 1.0000 1.0000
0.000 0.1037 0.00955 0.00229 -0.0180 1.0000 1.0000
0.250 0.1294 0.00959 0.00230 -0.0177 1.0000 1.0000
0.500 0.1549 0.00966 0.00236 -0.0175 1.0000 1.0000
0.750 0.1800 0.00975 0.00246 -0.0173 1.0000 1.0000
1.000 0.2048 0.00988 0.00264 -0.0172 1.0000 1.0000
1.250 0.2287 0.01009 0.00291 -0.0172 1.0000 1.0000
1.500 0.2662 0.01037 0.00328 -0.0203 0.9882 1.0000
1.750 0.3284 0.01046 0.00350 -0.0271 0.9457 1.0000
2.000 0.3739 0.01050 0.00359 -0.0297 0.8916 1.0000
2.250 0.4034 0.01065 0.00367 -0.0286 0.8345 1.0000
2.500 0.4264 0.01092 0.00380 -0.0263 0.7804 1.0000
2.750 0.4486 0.01130 0.00404 -0.0240 0.7293 1.0000
3.000 0.4713 0.01170 0.00430 -0.0221 0.6757 1.0000
3.250 0.4943 0.01198 0.00446 -0.0204 0.6131 1.0000
3.500 0.5170 0.01235 0.00457 -0.0187 0.5336 1.0000
3.750 0.5394 0.01301 0.00478 -0.0172 0.4344 1.0000
4.000 0.5621 0.01401 0.00528 -0.0161 0.3352 1.0000
4.250 0.5856 0.01514 0.00595 -0.0155 0.2621 1.0000
4.500 0.6100 0.01627 0.00681 -0.0149 0.2146 1.0000
4.750 0.6345 0.01742 0.00771 -0.0144 0.1815 1.0000
5.000 0.6598 0.01856 0.00882 -0.0139 0.1565 1.0000
5.250 0.6853 0.01985 0.01014 -0.0133 0.1369 1.0000
5.500 0.7107 0.02109 0.01142 -0.0128 0.1196 1.0000
5.750 0.7365 0.02280 0.01325 -0.0122 0.1076 1.0000
6.000 0.7616 0.02431 0.01489 -0.0118 0.0948 1.0000
6.250 0.7863 0.02665 0.01732 -0.0113 0.0870 1.0000
6.500 0.8114 0.02885 0.02012 -0.0105 0.0800 1.0000
6.750 0.8339 0.03135 0.02288 -0.0101 0.0728 1.0000
7.000 0.8556 0.03511 0.02739 -0.0094 0.0700 1.0000
7.250 0.8739 0.03987 0.03287 -0.0089 0.0691 1.0000
7.500 0.8891 0.04485 0.03846 -0.0088 0.0677 1.0000
7.750 0.9062 0.04789 0.04124 -0.0088 0.0620 1.0000
8.000 0.9187 0.05287 0.04691 -0.0088 0.0633 1.0000
8.250 0.8518 0.08962 0.08509 -0.0403 0.1470 1.0000
8.500 0.8746 0.09161 0.08713 -0.0308 0.1408 1.0000
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Polar data table (+)
Polar graphs
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