AG47ct -02f rot. (ag47ct02r-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG47ct -02f rot. (ag47ct02r-il) Reynolds number: 500,000 Max Cl/Cd: 65.36 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag47ct02r-il-500000.txt Download as CSV file: xf-ag47ct02r-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6248 0.10397 0.10179 0.0286 1.0000 0.0113
-8.250 -0.6209 0.09982 0.09765 0.0262 1.0000 0.0113
-8.000 -0.6289 0.09351 0.09139 0.0242 1.0000 0.0118
-7.750 -0.6245 0.09016 0.08806 0.0229 1.0000 0.0121
-7.500 -0.6181 0.08661 0.08450 0.0204 1.0000 0.0125
-7.250 -0.6084 0.08244 0.08034 0.0162 1.0000 0.0129
-7.000 -0.5963 0.07780 0.07569 0.0109 1.0000 0.0134
-6.750 -0.5815 0.07274 0.07061 0.0050 1.0000 0.0140
-6.500 -0.5638 0.06731 0.06514 -0.0012 1.0000 0.0147
-6.250 -0.5404 0.06140 0.05914 -0.0080 1.0000 0.0162
-6.000 -0.5073 0.05646 0.05403 -0.0136 1.0000 0.0174
-5.750 -0.4840 0.05123 0.04863 -0.0170 1.0000 0.0175
-5.500 -0.4613 0.04617 0.04335 -0.0195 1.0000 0.0176
-5.250 -0.4468 0.03672 0.03357 -0.0234 1.0000 0.0188
-5.000 -0.4246 0.03399 0.03072 -0.0242 1.0000 0.0195
-4.750 -0.4006 0.03118 0.02773 -0.0249 1.0000 0.0204
-4.500 -0.3751 0.02824 0.02456 -0.0254 1.0000 0.0218
-4.250 -0.3482 0.02534 0.02133 -0.0255 1.0000 0.0238
-4.000 -0.3179 0.02556 0.02126 -0.0245 1.0000 0.0267
-3.750 -0.2910 0.01535 0.01004 -0.0242 1.0000 0.0141
-3.500 -0.2632 0.01264 0.00689 -0.0234 1.0000 0.0131
-3.250 -0.2360 0.01151 0.00563 -0.0230 1.0000 0.0141
-3.000 -0.2089 0.01065 0.00468 -0.0226 1.0000 0.0155
-2.750 -0.1817 0.01026 0.00425 -0.0222 1.0000 0.0173
-2.500 -0.1549 0.00904 0.00292 -0.0218 1.0000 0.0201
-2.250 -0.1275 0.00852 0.00238 -0.0215 1.0000 0.0251
-2.000 -0.1002 0.00802 0.00187 -0.0212 1.0000 0.0382
-1.750 -0.0731 0.00743 0.00153 -0.0211 1.0000 0.0961
-1.500 -0.0463 0.00688 0.00138 -0.0211 1.0000 0.2036
-1.250 -0.0199 0.00607 0.00126 -0.0212 1.0000 0.4100
-1.000 0.0040 0.00497 0.00124 -0.0207 1.0000 0.7146
-0.750 0.0313 0.00428 0.00122 -0.0197 1.0000 1.0000
-0.500 0.0630 0.00428 0.00117 -0.0205 0.9940 1.0000
-0.250 0.1083 0.00430 0.00109 -0.0241 0.9498 1.0000
0.000 0.1390 0.00444 0.00098 -0.0240 0.8562 1.0000
0.250 0.1625 0.00474 0.00093 -0.0226 0.7837 1.0000
0.500 0.1882 0.00498 0.00093 -0.0219 0.7444 1.0000
0.750 0.2147 0.00517 0.00095 -0.0215 0.7174 1.0000
1.000 0.2417 0.00534 0.00099 -0.0211 0.6948 1.0000
1.250 0.2690 0.00544 0.00101 -0.0209 0.6682 1.0000
1.500 0.2962 0.00555 0.00103 -0.0206 0.6363 1.0000
1.750 0.3231 0.00571 0.00105 -0.0202 0.5975 1.0000
2.000 0.3500 0.00592 0.00108 -0.0199 0.5527 1.0000
2.250 0.3767 0.00618 0.00114 -0.0196 0.4997 1.0000
2.500 0.4035 0.00648 0.00123 -0.0194 0.4438 1.0000
2.750 0.4301 0.00684 0.00136 -0.0192 0.3803 1.0000
3.000 0.4569 0.00721 0.00151 -0.0191 0.3234 1.0000
3.250 0.4836 0.00761 0.00168 -0.0190 0.2671 1.0000
3.500 0.5103 0.00801 0.00188 -0.0189 0.2178 1.0000
3.750 0.5372 0.00839 0.00210 -0.0188 0.1798 1.0000
4.000 0.5640 0.00876 0.00237 -0.0186 0.1464 1.0000
4.250 0.5908 0.00914 0.00263 -0.0185 0.1197 1.0000
4.500 0.6176 0.00953 0.00294 -0.0184 0.1001 1.0000
4.750 0.6445 0.00989 0.00326 -0.0182 0.0845 1.0000
5.000 0.6712 0.01027 0.00365 -0.0180 0.0719 1.0000
5.250 0.6977 0.01073 0.00408 -0.0178 0.0611 1.0000
5.500 0.7244 0.01113 0.00447 -0.0176 0.0519 1.0000
5.750 0.7510 0.01155 0.00495 -0.0174 0.0453 1.0000
6.000 0.7766 0.01229 0.00572 -0.0171 0.0378 1.0000
6.250 0.8034 0.01259 0.00608 -0.0169 0.0333 1.0000
6.500 0.8277 0.01377 0.00733 -0.0164 0.0276 1.0000
6.750 0.8540 0.01422 0.00788 -0.0161 0.0256 1.0000
7.000 0.8796 0.01491 0.00868 -0.0158 0.0231 1.0000
7.250 0.9046 0.01572 0.00955 -0.0154 0.0207 1.0000
7.500 0.9261 0.01786 0.01194 -0.0146 0.0185 1.0000
7.750 0.9508 0.01878 0.01303 -0.0142 0.0176 1.0000
8.000 0.9745 0.02009 0.01454 -0.0136 0.0166 1.0000
8.250 0.9978 0.02139 0.01605 -0.0131 0.0155 1.0000
8.500 1.0218 0.02211 0.01686 -0.0129 0.0142 1.0000
8.750 1.0425 0.02386 0.01878 -0.0124 0.0130 1.0000
9.000 1.0489 0.03029 0.02596 -0.0113 0.0121 1.0000
9.250 1.0685 0.03193 0.02788 -0.0109 0.0117 1.0000
9.500 1.0816 0.03515 0.03149 -0.0104 0.0113 1.0000
9.750 1.0876 0.03958 0.03641 -0.0101 0.0109 1.0000
10.000 1.0860 0.04484 0.04210 -0.0105 0.0105 1.0000
10.250 1.0712 0.05166 0.04933 -0.0126 0.0105 1.0000
10.500 1.0450 0.05999 0.05790 -0.0201 0.0109 1.0000
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Polar data table (+)
Polar graphs
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