AG47c -03f (ag47c03-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG47c -03f (ag47c03-il) Reynolds number: 50,000 Max Cl/Cd: 30.72 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag47c03-il-50000-n5.txt Download as CSV file: xf-ag47c03-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6410 0.12755 0.12071 0.0358 1.0000 0.0879
-8.250 -0.6457 0.12532 0.11856 0.0313 1.0000 0.0893
-8.000 -0.6493 0.12272 0.11605 0.0267 1.0000 0.0898
-7.750 -0.6266 0.11579 0.10908 0.0322 1.0000 0.0946
-7.500 -0.6220 0.11220 0.10554 0.0307 1.0000 0.0978
-7.250 -0.6234 0.10925 0.10266 0.0268 1.0000 0.1018
-7.000 -0.6288 0.10662 0.10013 0.0179 1.0000 0.1034
-6.750 -0.6178 0.10130 0.09486 0.0199 1.0000 0.1048
-6.500 -0.6074 0.09696 0.09054 0.0202 1.0000 0.1069
-6.250 -0.5985 0.09284 0.08644 0.0179 1.0000 0.1092
-5.750 -0.5672 0.07871 0.07210 -0.0021 1.0000 0.0636
-5.500 -0.5496 0.07265 0.06592 -0.0045 1.0000 0.0485
-5.250 -0.5359 0.06818 0.06141 -0.0060 1.0000 0.0463
-5.000 -0.5184 0.06311 0.05623 -0.0093 1.0000 0.0442
-4.750 -0.4981 0.05769 0.05060 -0.0132 1.0000 0.0422
-4.500 -0.4749 0.05200 0.04457 -0.0169 1.0000 0.0402
-4.250 -0.4488 0.04636 0.03837 -0.0200 1.0000 0.0385
-4.000 -0.4225 0.04186 0.03328 -0.0217 1.0000 0.0378
-3.750 -0.3996 0.03864 0.02987 -0.0225 1.0000 0.0397
-3.500 -0.3740 0.03572 0.02654 -0.0231 1.0000 0.0427
-3.250 -0.3463 0.03257 0.02285 -0.0236 1.0000 0.0448
-3.000 -0.3179 0.02958 0.01930 -0.0236 1.0000 0.0458
-2.750 -0.2892 0.02697 0.01615 -0.0233 1.0000 0.0475
-2.500 -0.2615 0.02480 0.01365 -0.0229 1.0000 0.0519
-2.250 -0.2343 0.02321 0.01184 -0.0224 1.0000 0.0599
-2.000 -0.2070 0.02145 0.00991 -0.0216 1.0000 0.0662
-1.750 -0.1801 0.02020 0.00852 -0.0211 1.0000 0.0832
-1.500 -0.1527 0.01888 0.00716 -0.0207 1.0000 0.1080
-1.250 -0.1256 0.01737 0.00601 -0.0206 1.0000 0.1762
-1.000 -0.1074 0.01471 0.00538 -0.0191 1.0000 0.5568
-0.750 -0.0697 0.01349 0.00470 -0.0188 1.0000 1.0000
-0.500 -0.0431 0.01344 0.00422 -0.0186 1.0000 1.0000
-0.250 -0.0166 0.01341 0.00389 -0.0183 1.0000 1.0000
0.000 0.0097 0.01339 0.00363 -0.0181 1.0000 1.0000
0.250 0.0360 0.01339 0.00344 -0.0178 1.0000 1.0000
0.500 0.0621 0.01340 0.00328 -0.0176 1.0000 1.0000
0.750 0.0880 0.01343 0.00321 -0.0174 1.0000 1.0000
1.000 0.1136 0.01348 0.00319 -0.0173 1.0000 1.0000
1.250 0.1389 0.01355 0.00323 -0.0171 1.0000 1.0000
1.500 0.1637 0.01365 0.00333 -0.0169 1.0000 1.0000
1.750 0.1875 0.01379 0.00351 -0.0168 1.0000 1.0000
2.000 0.2173 0.01401 0.00378 -0.0181 0.9891 1.0000
2.250 0.2659 0.01426 0.00408 -0.0226 0.9454 1.0000
2.500 0.3111 0.01448 0.00437 -0.0259 0.8998 1.0000
2.750 0.3492 0.01472 0.00461 -0.0272 0.8530 1.0000
3.000 0.3794 0.01501 0.00484 -0.0267 0.8083 1.0000
3.250 0.4045 0.01536 0.00509 -0.0251 0.7663 1.0000
3.500 0.4277 0.01578 0.00545 -0.0231 0.7262 1.0000
3.750 0.4506 0.01623 0.00582 -0.0213 0.6848 1.0000
4.000 0.4738 0.01655 0.00616 -0.0197 0.6365 1.0000
4.250 0.4968 0.01683 0.00641 -0.0180 0.5829 1.0000
4.500 0.5195 0.01716 0.00662 -0.0164 0.5198 1.0000
4.750 0.5421 0.01765 0.00694 -0.0148 0.4454 1.0000
5.000 0.5649 0.01839 0.00735 -0.0137 0.3639 1.0000
5.250 0.5884 0.01938 0.00800 -0.0130 0.2880 1.0000
5.500 0.6124 0.02051 0.00888 -0.0127 0.2308 1.0000
5.750 0.6374 0.02172 0.00994 -0.0125 0.1909 1.0000
6.000 0.6621 0.02295 0.01120 -0.0122 0.1626 1.0000
6.250 0.6863 0.02425 0.01246 -0.0117 0.1412 1.0000
6.500 0.7107 0.02556 0.01391 -0.0112 0.1226 1.0000
6.750 0.7352 0.02714 0.01561 -0.0105 0.1100 1.0000
7.000 0.7592 0.02861 0.01724 -0.0101 0.0958 1.0000
7.250 0.7831 0.03053 0.01934 -0.0095 0.0875 1.0000
7.500 0.8073 0.03261 0.02177 -0.0089 0.0790 1.0000
7.750 0.8300 0.03481 0.02436 -0.0086 0.0701 1.0000
8.000 0.8522 0.03739 0.02724 -0.0082 0.0653 1.0000
8.250 0.8724 0.04094 0.03125 -0.0079 0.0620 1.0000
8.500 0.8897 0.04490 0.03597 -0.0079 0.0571 1.0000
8.750 0.9070 0.04735 0.03862 -0.0079 0.0524 1.0000
9.000 0.9194 0.05183 0.04347 -0.0082 0.0507 1.0000
9.250 0.9244 0.05777 0.05017 -0.0094 0.0500 1.0000
9.500 0.9239 0.06402 0.05692 -0.0114 0.0496 1.0000
9.750 0.9183 0.07045 0.06368 -0.0143 0.0495 1.0000
10.000 0.9088 0.07700 0.07037 -0.0181 0.0496 1.0000
10.250 0.8965 0.08360 0.07705 -0.0230 0.0499 1.0000
10.500 0.8856 0.09089 0.08434 -0.0291 0.0503 1.0000
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Polar data table (+)
Polar graphs
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