AG03 (flat aft bottom) (ag03-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG03 (flat aft bottom) (ag03-il) Reynolds number: 50,000 Max Cl/Cd: 32.7 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag03-il-50000.txt Download as CSV file: xf-ag03-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AG03 (flat aft bottom)
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5446 0.11083 0.10427 0.0130 1.0000 0.1624
-8.000 -0.5347 0.10692 0.10037 0.0132 1.0000 0.1710
-7.750 -0.5505 0.10616 0.09977 0.0062 1.0000 0.1744
-7.500 -0.5297 0.10037 0.09398 0.0104 1.0000 0.1859
-7.250 -0.5224 0.09639 0.09005 0.0102 1.0000 0.1942
-7.000 -0.5267 0.09389 0.08766 0.0036 1.0000 0.2030
-6.750 -0.5214 0.09074 0.08453 0.0004 1.0000 0.2162
-6.500 -0.5105 0.08638 0.08024 0.0019 1.0000 0.2310
-6.250 -0.4980 0.08226 0.07617 0.0044 1.0000 0.2478
-6.000 -0.4888 0.07885 0.07281 0.0043 1.0000 0.2680
-5.750 -0.4806 0.07526 0.06928 0.0039 1.0000 0.2894
-5.500 -0.4723 0.07195 0.06598 0.0039 1.0000 0.3160
-5.250 -0.4619 0.06856 0.06266 0.0062 1.0000 0.3451
-4.250 -0.3279 0.04490 0.03725 -0.0333 1.0000 0.1611
-4.000 -0.2922 0.03917 0.03070 -0.0354 1.0000 0.1179
-3.750 -0.2618 0.03530 0.02600 -0.0357 1.0000 0.1053
-3.500 -0.2378 0.03200 0.02264 -0.0355 1.0000 0.1087
-3.250 -0.2108 0.02932 0.01957 -0.0351 1.0000 0.1123
-3.000 -0.1822 0.02667 0.01641 -0.0343 1.0000 0.1146
-2.750 -0.1550 0.02453 0.01397 -0.0335 1.0000 0.1292
-2.500 -0.1273 0.02236 0.01162 -0.0326 1.0000 0.1503
-2.250 -0.1002 0.02037 0.00965 -0.0314 1.0000 0.1989
-2.000 -0.0735 0.01789 0.00784 -0.0306 1.0000 0.3201
-1.750 -0.0372 0.01438 0.00621 -0.0291 1.0000 1.0000
-1.500 -0.0137 0.01438 0.00570 -0.0282 1.0000 1.0000
-1.250 0.0095 0.01440 0.00534 -0.0274 1.0000 1.0000
-1.000 0.0324 0.01445 0.00504 -0.0267 1.0000 1.0000
-0.750 0.0552 0.01453 0.00487 -0.0260 1.0000 1.0000
-0.500 0.0778 0.01463 0.00477 -0.0253 1.0000 1.0000
-0.250 0.1001 0.01477 0.00473 -0.0247 1.0000 1.0000
0.000 0.1223 0.01496 0.00477 -0.0241 1.0000 1.0000
0.250 0.1443 0.01518 0.00486 -0.0237 1.0000 1.0000
0.500 0.1661 0.01547 0.00505 -0.0233 1.0000 1.0000
0.750 0.1875 0.01581 0.00533 -0.0231 1.0000 1.0000
1.000 0.2084 0.01623 0.00571 -0.0230 1.0000 1.0000
1.250 0.2287 0.01675 0.00618 -0.0231 1.0000 1.0000
1.500 0.2483 0.01737 0.00680 -0.0233 1.0000 1.0000
1.750 0.2671 0.01813 0.00757 -0.0238 1.0000 1.0000
2.000 0.3037 0.01906 0.00857 -0.0280 0.9902 1.0000
2.250 0.3896 0.01983 0.00955 -0.0402 0.9517 1.0000
2.500 0.4700 0.02002 0.01001 -0.0498 0.9112 1.0000
2.750 0.5265 0.01992 0.01013 -0.0534 0.8690 1.0000
3.000 0.5645 0.01982 0.01022 -0.0529 0.8262 1.0000
3.250 0.5921 0.01982 0.01026 -0.0503 0.7830 1.0000
3.500 0.6155 0.01992 0.01035 -0.0471 0.7393 1.0000
3.750 0.6374 0.02013 0.01050 -0.0437 0.6950 1.0000
4.000 0.6590 0.02046 0.01080 -0.0406 0.6501 1.0000
4.250 0.6804 0.02096 0.01123 -0.0379 0.6028 1.0000
4.500 0.7023 0.02151 0.01166 -0.0354 0.5571 1.0000
4.750 0.7246 0.02216 0.01215 -0.0331 0.5125 1.0000
5.000 0.7468 0.02299 0.01289 -0.0313 0.4668 1.0000
5.250 0.7691 0.02390 0.01375 -0.0295 0.4228 1.0000
5.500 0.7914 0.02494 0.01468 -0.0279 0.3806 1.0000
5.750 0.8138 0.02612 0.01578 -0.0265 0.3406 1.0000
6.000 0.8365 0.02745 0.01695 -0.0251 0.3045 1.0000
6.250 0.8588 0.02904 0.01864 -0.0239 0.2703 1.0000
6.500 0.8814 0.03080 0.02052 -0.0228 0.2416 1.0000
6.750 0.9035 0.03275 0.02260 -0.0218 0.2166 1.0000
7.000 0.9263 0.03506 0.02502 -0.0208 0.1977 1.0000
7.250 0.9461 0.03740 0.02767 -0.0198 0.1782 1.0000
7.500 0.9664 0.04063 0.03122 -0.0189 0.1664 1.0000
7.750 0.9856 0.04377 0.03460 -0.0180 0.1546 1.0000
8.000 1.0025 0.04673 0.03779 -0.0170 0.1417 1.0000
8.250 1.0079 0.05233 0.04431 -0.0163 0.1386 1.0000
8.500 1.0089 0.05843 0.05105 -0.0163 0.1373 1.0000
8.750 1.0039 0.06494 0.05804 -0.0169 0.1372 1.0000
9.000 0.9935 0.07174 0.06515 -0.0184 0.1382 1.0000
9.250 0.9816 0.07851 0.07210 -0.0204 0.1397 1.0000
9.500 0.9708 0.08511 0.07878 -0.0225 0.1410 1.0000
9.750 0.9613 0.09149 0.08521 -0.0245 0.1422 1.0000
10.000 0.8456 0.12725 0.12032 -0.0676 0.3188 1.0000
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Polar data table (+)
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