AG46c -03f (ag46c03-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG46c -03f (ag46c03-il) Reynolds number: 50,000 Max Cl/Cd: 30.81 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag46c03-il-50000.txt Download as CSV file: xf-ag46c03-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AG46c -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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.5951 0.11208 0.10566 0.0262 1.0000 0.1803
-7.000 -0.5789 0.10670 0.10028 0.0278 1.0000 0.1881
-6.750 -0.5920 0.10548 0.09921 0.0222 1.0000 0.1948
-6.500 -0.5728 0.09997 0.09369 0.0252 1.0000 0.2055
-6.000 -0.5670 0.09294 0.08681 0.0201 1.0000 0.2251
-5.500 -0.5498 0.08530 0.07928 0.0181 1.0000 0.2538
-5.250 -0.5381 0.08161 0.07563 0.0195 1.0000 0.2740
-5.000 -0.5300 0.07804 0.07212 0.0190 1.0000 0.2977
-4.750 -0.5202 0.07462 0.06871 0.0202 1.0000 0.3262
-4.500 -0.5095 0.07131 0.06546 0.0224 1.0000 0.3581
-3.500 -0.3677 0.04379 0.03607 -0.0264 1.0000 0.1545
-3.250 -0.3319 0.03830 0.02974 -0.0289 1.0000 0.1240
-3.000 -0.3028 0.03418 0.02518 -0.0296 1.0000 0.1158
-2.750 -0.2730 0.03096 0.02142 -0.0299 1.0000 0.1156
-2.500 -0.2438 0.02835 0.01837 -0.0298 1.0000 0.1210
-2.250 -0.2131 0.02580 0.01524 -0.0295 1.0000 0.1240
-2.000 -0.1846 0.02366 0.01291 -0.0289 1.0000 0.1376
-1.750 -0.1565 0.02161 0.01081 -0.0282 1.0000 0.1589
-1.500 -0.1288 0.01977 0.00905 -0.0273 1.0000 0.2068
-1.250 -0.1034 0.01672 0.00717 -0.0262 1.0000 0.3715
-1.000 -0.0696 0.01383 0.00580 -0.0237 1.0000 1.0000
-0.750 -0.0435 0.01378 0.00526 -0.0234 1.0000 1.0000
-0.500 -0.0177 0.01375 0.00483 -0.0231 1.0000 1.0000
-0.250 0.0079 0.01374 0.00454 -0.0228 1.0000 1.0000
0.000 0.0331 0.01375 0.00432 -0.0225 1.0000 1.0000
0.250 0.0579 0.01378 0.00418 -0.0223 1.0000 1.0000
0.500 0.0822 0.01385 0.00409 -0.0220 1.0000 1.0000
0.750 0.1055 0.01396 0.00411 -0.0217 1.0000 1.0000
1.000 0.1276 0.01414 0.00421 -0.0215 1.0000 1.0000
1.250 0.1485 0.01441 0.00442 -0.0213 1.0000 1.0000
1.500 0.1685 0.01477 0.00472 -0.0213 1.0000 1.0000
1.750 0.1888 0.01523 0.00512 -0.0216 1.0000 1.0000
2.000 0.2093 0.01578 0.00562 -0.0221 1.0000 1.0000
2.250 0.2296 0.01643 0.00625 -0.0230 1.0000 1.0000
2.500 0.2735 0.01719 0.00706 -0.0283 0.9860 1.0000
2.750 0.3529 0.01778 0.00782 -0.0391 0.9486 1.0000
3.000 0.4251 0.01803 0.00826 -0.0470 0.9103 1.0000
3.250 0.4733 0.01819 0.00860 -0.0493 0.8708 1.0000
3.500 0.5034 0.01848 0.00894 -0.0478 0.8310 1.0000
3.750 0.5265 0.01887 0.00934 -0.0450 0.7919 1.0000
4.000 0.5470 0.01936 0.00980 -0.0417 0.7531 1.0000
4.250 0.5668 0.01993 0.01033 -0.0383 0.7144 1.0000
4.500 0.5868 0.02059 0.01105 -0.0354 0.6717 1.0000
4.750 0.6072 0.02099 0.01143 -0.0324 0.6291 1.0000
5.000 0.6281 0.02121 0.01159 -0.0294 0.5858 1.0000
5.250 0.6495 0.02146 0.01173 -0.0266 0.5396 1.0000
5.500 0.6714 0.02187 0.01200 -0.0241 0.4902 1.0000
5.750 0.6938 0.02252 0.01252 -0.0220 0.4409 1.0000
6.000 0.7167 0.02344 0.01327 -0.0204 0.3934 1.0000
6.250 0.7401 0.02456 0.01426 -0.0190 0.3509 1.0000
6.500 0.7637 0.02586 0.01548 -0.0179 0.3127 1.0000
6.750 0.7876 0.02731 0.01686 -0.0168 0.2801 1.0000
7.000 0.8115 0.02897 0.01857 -0.0160 0.2514 1.0000
7.250 0.8351 0.03083 0.02056 -0.0152 0.2251 1.0000
7.500 0.8583 0.03316 0.02314 -0.0145 0.2033 1.0000
7.750 0.8812 0.03546 0.02557 -0.0138 0.1837 1.0000
8.000 0.9031 0.03812 0.02835 -0.0131 0.1668 1.0000
8.250 0.9235 0.04164 0.03237 -0.0126 0.1552 1.0000
8.500 0.9424 0.04460 0.03561 -0.0120 0.1409 1.0000
8.750 0.9528 0.05034 0.04226 -0.0124 0.1366 1.0000
9.000 0.9584 0.05678 0.04938 -0.0135 0.1351 1.0000
9.250 0.9575 0.06376 0.05686 -0.0156 0.1350 1.0000
9.500 0.9510 0.07115 0.06458 -0.0187 0.1363 1.0000
9.750 0.9430 0.07842 0.07201 -0.0222 0.1381 1.0000
10.000 0.9366 0.08533 0.07900 -0.0253 0.1394 1.0000
10.250 0.9333 0.09192 0.08562 -0.0279 0.1402 1.0000
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Polar data table (+)
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