AG47ct -02f rot. (ag47ct02r-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG47ct -02f rot. (ag47ct02r-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.87 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag47ct02r-il-1000000-n5.txt Download as CSV file: xf-ag47ct02r-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6428 0.09588 0.09434 0.0304 1.0000 0.0031
-8.000 -0.6407 0.09158 0.09006 0.0278 1.0000 0.0032
-7.750 -0.6384 0.08707 0.08556 0.0244 1.0000 0.0033
-7.500 -0.6310 0.08160 0.08010 0.0183 1.0000 0.0035
-7.250 -0.6194 0.07529 0.07378 0.0107 1.0000 0.0037
-7.000 -0.6042 0.06838 0.06684 0.0025 1.0000 0.0038
-6.750 -0.5860 0.06143 0.05982 -0.0049 1.0000 0.0038
-6.500 -0.5655 0.05425 0.05252 -0.0116 1.0000 0.0039
-6.250 -0.5432 0.04683 0.04492 -0.0170 1.0000 0.0039
-6.000 -0.5196 0.03966 0.03753 -0.0206 1.0000 0.0041
-5.750 -0.4957 0.03202 0.02955 -0.0230 1.0000 0.0042
-5.500 -0.4756 0.01710 0.01331 -0.0245 1.0000 0.0040
-5.250 -0.4501 0.01419 0.00991 -0.0243 1.0000 0.0039
-5.000 -0.4238 0.01245 0.00784 -0.0240 1.0000 0.0040
-4.750 -0.3972 0.01123 0.00640 -0.0238 1.0000 0.0040
-4.500 -0.3703 0.01033 0.00534 -0.0235 1.0000 0.0041
-4.250 -0.3434 0.00965 0.00455 -0.0232 1.0000 0.0042
-4.000 -0.3164 0.00887 0.00364 -0.0229 1.0000 0.0045
-3.750 -0.2892 0.00831 0.00302 -0.0227 1.0000 0.0051
-3.500 -0.2619 0.00801 0.00269 -0.0225 1.0000 0.0057
-3.250 -0.2343 0.00772 0.00237 -0.0224 0.9991 0.0062
-3.000 -0.1987 0.00744 0.00205 -0.0240 0.9738 0.0068
-2.750 -0.1665 0.00726 0.00171 -0.0246 0.9028 0.0079
-2.500 -0.1441 0.00742 0.00151 -0.0231 0.7924 0.0101
-2.250 -0.1177 0.00743 0.00130 -0.0227 0.7408 0.0135
-1.750 -0.0628 0.00729 0.00104 -0.0223 0.7047 0.0276
-1.500 -0.0351 0.00714 0.00093 -0.0222 0.6914 0.0491
-1.250 -0.0073 0.00698 0.00083 -0.0221 0.6747 0.0783
-1.000 0.0203 0.00685 0.00074 -0.0220 0.6535 0.1138
-0.750 0.0479 0.00668 0.00067 -0.0220 0.6283 0.1687
-0.500 0.0753 0.00652 0.00060 -0.0219 0.5985 0.2368
-0.250 0.1026 0.00630 0.00056 -0.0219 0.5663 0.3360
0.000 0.1297 0.00607 0.00054 -0.0219 0.5310 0.4517
0.250 0.1567 0.00587 0.00054 -0.0219 0.4926 0.5656
0.500 0.1830 0.00561 0.00056 -0.0216 0.4526 0.7038
0.750 0.2072 0.00536 0.00060 -0.0208 0.4120 0.8390
1.000 0.2328 0.00523 0.00063 -0.0199 0.3716 0.9765
1.250 0.2633 0.00544 0.00067 -0.0205 0.3285 1.0000
1.500 0.2909 0.00564 0.00072 -0.0204 0.2930 1.0000
1.750 0.3183 0.00587 0.00079 -0.0203 0.2537 1.0000
2.000 0.3458 0.00608 0.00087 -0.0202 0.2233 1.0000
2.250 0.3733 0.00630 0.00096 -0.0202 0.1913 1.0000
2.500 0.4008 0.00650 0.00106 -0.0201 0.1692 1.0000
2.750 0.4283 0.00670 0.00118 -0.0200 0.1466 1.0000
3.000 0.4558 0.00692 0.00130 -0.0199 0.1250 1.0000
3.250 0.4833 0.00711 0.00143 -0.0198 0.1103 1.0000
3.500 0.5107 0.00731 0.00157 -0.0197 0.0959 1.0000
3.750 0.5381 0.00753 0.00174 -0.0196 0.0820 1.0000
4.000 0.5656 0.00773 0.00190 -0.0195 0.0725 1.0000
4.250 0.5929 0.00796 0.00208 -0.0194 0.0618 1.0000
4.500 0.6202 0.00817 0.00227 -0.0193 0.0541 1.0000
4.750 0.6475 0.00839 0.00248 -0.0192 0.0476 1.0000
5.000 0.6746 0.00866 0.00272 -0.0190 0.0396 1.0000
5.250 0.7018 0.00887 0.00295 -0.0189 0.0356 1.0000
5.500 0.7287 0.00917 0.00321 -0.0188 0.0294 1.0000
5.750 0.7558 0.00942 0.00348 -0.0186 0.0257 1.0000
6.000 0.7826 0.00972 0.00379 -0.0185 0.0219 1.0000
6.250 0.8094 0.01004 0.00413 -0.0183 0.0185 1.0000
6.500 0.8362 0.01034 0.00446 -0.0181 0.0168 1.0000
6.750 0.8627 0.01070 0.00482 -0.0180 0.0145 1.0000
7.000 0.8890 0.01115 0.00531 -0.0177 0.0121 1.0000
7.250 0.9155 0.01147 0.00570 -0.0176 0.0113 1.0000
7.500 0.9418 0.01186 0.00615 -0.0174 0.0104 1.0000
7.750 0.9678 0.01230 0.00662 -0.0172 0.0095 1.0000
8.000 0.9934 0.01282 0.00720 -0.0169 0.0084 1.0000
8.250 1.0187 0.01347 0.00793 -0.0166 0.0075 1.0000
8.500 1.0445 0.01391 0.00845 -0.0164 0.0072 1.0000
8.750 1.0699 0.01443 0.00905 -0.0161 0.0068 1.0000
9.000 1.0951 0.01498 0.00970 -0.0159 0.0064 1.0000
9.250 1.1201 0.01552 0.01031 -0.0156 0.0059 1.0000
9.500 1.1448 0.01611 0.01096 -0.0154 0.0053 1.0000
9.750 1.1681 0.01709 0.01206 -0.0150 0.0046 1.0000
10.000 1.1923 0.01774 0.01281 -0.0147 0.0044 1.0000
10.250 1.2161 0.01844 0.01362 -0.0144 0.0042 1.0000
10.500 1.2395 0.01922 0.01452 -0.0141 0.0039 1.0000
10.750 1.2624 0.02005 0.01546 -0.0137 0.0037 1.0000
11.000 1.2849 0.02091 0.01646 -0.0133 0.0034 1.0000
11.250 1.3069 0.02183 0.01749 -0.0129 0.0032 1.0000
11.500 1.3279 0.02290 0.01868 -0.0125 0.0029 1.0000
11.750 1.3465 0.02440 0.02035 -0.0120 0.0026 1.0000
12.000 1.3633 0.02615 0.02231 -0.0114 0.0025 1.0000
12.250 1.3809 0.02758 0.02391 -0.0109 0.0024 1.0000
12.500 1.3969 0.02918 0.02570 -0.0103 0.0023 1.0000
12.750 1.4107 0.03100 0.02771 -0.0097 0.0023 1.0000
13.000 1.4218 0.03307 0.02999 -0.0091 0.0022 1.0000
13.250 1.4292 0.03546 0.03258 -0.0085 0.0021 1.0000
13.500 1.4318 0.03823 0.03557 -0.0081 0.0020 1.0000
13.750 1.4235 0.04155 0.03909 -0.0075 0.0020 1.0000
14.000 1.4038 0.04768 0.04544 -0.0120 0.0020 1.0000
14.250 1.3416 0.06876 0.06688 -0.0312 0.0022 1.0000
14.500 1.2018 0.10312 0.10140 -0.0507 0.0025 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG47ct -02f rot. (ag47ct02r-il)