AG47c -03f (ag47c03-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG47c -03f (ag47c03-il) Reynolds number: 500,000 Max Cl/Cd: 65.16 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag47c03-il-500000.txt Download as CSV file: xf-ag47c03-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG47c -03f
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6441 0.11477 0.11258 0.0373 1.0000 0.0108
-8.000 -0.6493 0.10848 0.10633 0.0354 1.0000 0.0111
-7.750 -0.6454 0.10505 0.10291 0.0351 1.0000 0.0115
-7.500 -0.6403 0.10177 0.09962 0.0343 1.0000 0.0118
-7.250 -0.6360 0.09826 0.09613 0.0327 1.0000 0.0121
-7.000 -0.6319 0.09463 0.09251 0.0307 1.0000 0.0124
-6.750 -0.6278 0.09082 0.08873 0.0282 1.0000 0.0128
-6.500 -0.6217 0.08672 0.08465 0.0244 1.0000 0.0132
-6.250 -0.6109 0.08207 0.07999 0.0190 1.0000 0.0140
-6.000 -0.5965 0.07685 0.07476 0.0124 1.0000 0.0149
-5.750 -0.5751 0.07086 0.06873 0.0040 1.0000 0.0159
-5.500 -0.5493 0.06549 0.06328 -0.0028 1.0000 0.0165
-5.250 -0.5265 0.06012 0.05780 -0.0078 1.0000 0.0167
-5.000 -0.5038 0.05470 0.05224 -0.0118 1.0000 0.0168
-4.750 -0.4810 0.04941 0.04677 -0.0149 1.0000 0.0168
-4.500 -0.4654 0.03951 0.03652 -0.0196 1.0000 0.0177
-4.250 -0.4441 0.03621 0.03310 -0.0208 1.0000 0.0184
-4.000 -0.4205 0.03332 0.03005 -0.0217 1.0000 0.0192
-3.750 -0.3953 0.03030 0.02682 -0.0224 1.0000 0.0203
-3.500 -0.3687 0.02717 0.02339 -0.0228 1.0000 0.0219
-3.250 -0.3384 0.02657 0.02250 -0.0221 1.0000 0.0254
-3.000 -0.3110 0.01769 0.01275 -0.0221 1.0000 0.0151
-2.750 -0.2826 0.01381 0.00827 -0.0215 1.0000 0.0131
-2.500 -0.2550 0.01233 0.00659 -0.0210 1.0000 0.0138
-2.250 -0.2275 0.01129 0.00542 -0.0206 1.0000 0.0149
-2.000 -0.1999 0.01093 0.00501 -0.0204 1.0000 0.0166
-1.750 -0.1729 0.00951 0.00346 -0.0200 1.0000 0.0183
-1.500 -0.1453 0.00879 0.00270 -0.0198 1.0000 0.0214
-1.250 -0.1174 0.00821 0.00207 -0.0195 1.0000 0.0291
-1.000 -0.0898 0.00772 0.00169 -0.0194 1.0000 0.0561
-0.750 -0.0624 0.00717 0.00148 -0.0194 1.0000 0.1381
-0.500 -0.0354 0.00653 0.00134 -0.0196 1.0000 0.2807
-0.250 -0.0065 0.00551 0.00127 -0.0204 0.9910 0.5559
0.000 0.0231 0.00441 0.00127 -0.0201 0.9178 0.8945
0.250 0.0565 0.00455 0.00112 -0.0204 0.8208 1.0000
0.500 0.0818 0.00479 0.00105 -0.0196 0.7764 1.0000
0.750 0.1084 0.00496 0.00102 -0.0191 0.7508 1.0000
1.000 0.1354 0.00513 0.00101 -0.0188 0.7317 1.0000
1.250 0.1626 0.00527 0.00103 -0.0185 0.7153 1.0000
1.500 0.1900 0.00541 0.00105 -0.0182 0.7002 1.0000
1.750 0.2176 0.00549 0.00107 -0.0180 0.6837 1.0000
2.000 0.2453 0.00553 0.00107 -0.0178 0.6653 1.0000
2.250 0.2729 0.00558 0.00106 -0.0176 0.6435 1.0000
2.500 0.3004 0.00566 0.00106 -0.0174 0.6169 1.0000
2.750 0.3278 0.00578 0.00107 -0.0172 0.5853 1.0000
3.000 0.3550 0.00596 0.00110 -0.0169 0.5454 1.0000
3.250 0.3821 0.00617 0.00115 -0.0167 0.5029 1.0000
3.500 0.4091 0.00645 0.00125 -0.0166 0.4492 1.0000
3.750 0.4361 0.00678 0.00137 -0.0165 0.3935 1.0000
4.000 0.4630 0.00715 0.00151 -0.0164 0.3345 1.0000
4.250 0.4898 0.00759 0.00170 -0.0163 0.2699 1.0000
4.500 0.5166 0.00803 0.00191 -0.0163 0.2156 1.0000
4.750 0.5435 0.00847 0.00218 -0.0163 0.1697 1.0000
5.000 0.5704 0.00889 0.00245 -0.0162 0.1334 1.0000
5.250 0.5974 0.00928 0.00275 -0.0162 0.1095 1.0000
5.500 0.6243 0.00968 0.00307 -0.0161 0.0912 1.0000
5.750 0.6511 0.01011 0.00347 -0.0160 0.0764 1.0000
6.000 0.6781 0.01045 0.00381 -0.0159 0.0664 1.0000
6.250 0.7050 0.01082 0.00421 -0.0157 0.0573 1.0000
6.500 0.7316 0.01133 0.00472 -0.0156 0.0490 1.0000
6.750 0.7581 0.01179 0.00518 -0.0154 0.0419 1.0000
7.000 0.7845 0.01232 0.00581 -0.0152 0.0362 1.0000
7.250 0.8107 0.01288 0.00639 -0.0151 0.0308 1.0000
7.500 0.8359 0.01382 0.00745 -0.0147 0.0273 1.0000
7.750 0.8619 0.01446 0.00818 -0.0144 0.0246 1.0000
8.000 0.8875 0.01514 0.00892 -0.0142 0.0220 1.0000
8.250 0.9095 0.01718 0.01119 -0.0136 0.0193 1.0000
8.500 0.9347 0.01800 0.01216 -0.0133 0.0184 1.0000
8.750 0.9589 0.01921 0.01355 -0.0128 0.0173 1.0000
9.000 0.9827 0.02048 0.01501 -0.0124 0.0161 1.0000
9.250 1.0070 0.02122 0.01584 -0.0122 0.0148 1.0000
9.500 1.0280 0.02310 0.01791 -0.0118 0.0134 1.0000
9.750 1.0392 0.02848 0.02395 -0.0110 0.0126 1.0000
10.000 1.0594 0.03024 0.02599 -0.0106 0.0122 1.0000
10.250 1.0745 0.03330 0.02948 -0.0102 0.0117 1.0000
10.500 1.0854 0.03697 0.03356 -0.0100 0.0111 1.0000
10.750 1.0945 0.04044 0.03737 -0.0101 0.0104 1.0000
11.000 1.1090 0.04207 0.03914 -0.0102 0.0097 1.0000
11.250 1.1198 0.04414 0.04137 -0.0106 0.0092 1.0000
11.500 1.1142 0.04893 0.04645 -0.0122 0.0090 1.0000
11.750 0.9611 0.09330 0.09135 -0.0479 0.0127 1.0000
12.000 0.9513 0.10124 0.09929 -0.0518 0.0129 1.0000
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Polar data table (+)
Polar graphs
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