AG13 (ag13-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG13 (ag13-il) Reynolds number: 200,000 Max Cl/Cd: 58.95 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag13-il-200000-n5.txt Download as CSV file: xf-ag13-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG13
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5693 0.11590 0.11242 0.0187 1.0000 0.0163
-9.000 -0.5686 0.11080 0.10734 0.0170 1.0000 0.0166
-8.750 -0.5652 0.10653 0.10305 0.0153 1.0000 0.0167
-7.750 -0.5456 0.09171 0.08830 0.0110 1.0000 0.0143
-7.500 -0.5420 0.08767 0.08429 0.0087 1.0000 0.0133
-7.250 -0.5364 0.08297 0.07964 0.0047 1.0000 0.0124
-7.000 -0.5270 0.07688 0.07356 -0.0019 1.0000 0.0114
-6.250 -0.4677 0.05404 0.05053 -0.0278 1.0000 0.0097
-6.000 -0.4443 0.04577 0.04202 -0.0350 1.0000 0.0096
-5.500 -0.3962 0.03299 0.02846 -0.0438 1.0000 0.0111
-5.250 -0.3712 0.03080 0.02604 -0.0449 1.0000 0.0125
-5.000 -0.3438 0.02592 0.02055 -0.0464 1.0000 0.0127
-4.750 -0.3159 0.02208 0.01608 -0.0470 1.0000 0.0126
-4.500 -0.2883 0.01939 0.01286 -0.0471 1.0000 0.0127
-4.250 -0.2609 0.01738 0.01047 -0.0469 1.0000 0.0130
-4.000 -0.2337 0.01580 0.00862 -0.0466 1.0000 0.0137
-3.750 -0.2067 0.01452 0.00711 -0.0463 1.0000 0.0146
-3.500 -0.1798 0.01354 0.00598 -0.0459 1.0000 0.0159
-3.250 -0.1532 0.01265 0.00506 -0.0458 1.0000 0.0202
-3.000 -0.1262 0.01200 0.00430 -0.0455 1.0000 0.0244
-2.750 -0.0991 0.01132 0.00357 -0.0452 1.0000 0.0333
-2.500 -0.0723 0.01077 0.00307 -0.0450 1.0000 0.0563
-2.250 -0.0457 0.01029 0.00277 -0.0449 1.0000 0.1027
-2.000 -0.0192 0.00982 0.00256 -0.0448 1.0000 0.1679
-1.750 0.0073 0.00941 0.00242 -0.0448 1.0000 0.2467
-1.500 0.0337 0.00904 0.00234 -0.0447 1.0000 0.3302
-1.250 0.0696 0.00865 0.00224 -0.0466 0.9892 0.4310
-1.000 0.1057 0.00824 0.00218 -0.0484 0.9735 0.5392
-0.500 0.1736 0.00700 0.00197 -0.0496 0.9286 1.0000
-0.250 0.2074 0.00703 0.00184 -0.0504 0.8958 1.0000
0.000 0.2374 0.00709 0.00174 -0.0504 0.8579 1.0000
0.250 0.2642 0.00721 0.00166 -0.0496 0.8174 1.0000
0.500 0.2899 0.00737 0.00162 -0.0487 0.7766 1.0000
0.750 0.3156 0.00756 0.00160 -0.0478 0.7360 1.0000
1.000 0.3415 0.00777 0.00160 -0.0471 0.6961 1.0000
1.250 0.3676 0.00800 0.00162 -0.0465 0.6570 1.0000
1.500 0.3939 0.00823 0.00167 -0.0459 0.6187 1.0000
1.750 0.4203 0.00848 0.00176 -0.0455 0.5810 1.0000
2.000 0.4467 0.00875 0.00184 -0.0450 0.5436 1.0000
2.250 0.4733 0.00901 0.00195 -0.0447 0.5070 1.0000
2.500 0.4999 0.00929 0.00208 -0.0443 0.4712 1.0000
2.750 0.5265 0.00958 0.00223 -0.0441 0.4356 1.0000
3.000 0.5531 0.00989 0.00243 -0.0438 0.4003 1.0000
3.250 0.5796 0.01021 0.00263 -0.0435 0.3654 1.0000
3.500 0.6062 0.01055 0.00285 -0.0433 0.3312 1.0000
3.750 0.6327 0.01090 0.00310 -0.0431 0.2986 1.0000
4.000 0.6592 0.01128 0.00337 -0.0429 0.2669 1.0000
4.250 0.6856 0.01167 0.00372 -0.0427 0.2367 1.0000
4.500 0.7119 0.01208 0.00406 -0.0425 0.2084 1.0000
4.750 0.7381 0.01252 0.00443 -0.0422 0.1808 1.0000
5.000 0.7642 0.01297 0.00484 -0.0420 0.1569 1.0000
5.250 0.7901 0.01348 0.00532 -0.0418 0.1329 1.0000
5.500 0.8160 0.01398 0.00582 -0.0415 0.1123 1.0000
5.750 0.8416 0.01455 0.00636 -0.0413 0.0933 1.0000
6.000 0.8672 0.01513 0.00695 -0.0410 0.0767 1.0000
6.250 0.8924 0.01577 0.00760 -0.0407 0.0619 1.0000
6.500 0.9175 0.01646 0.00832 -0.0403 0.0493 1.0000
6.750 0.9422 0.01722 0.00917 -0.0399 0.0385 1.0000
7.000 0.9664 0.01811 0.01013 -0.0395 0.0298 1.0000
7.250 0.9898 0.01915 0.01122 -0.0390 0.0226 1.0000
7.500 1.0135 0.02011 0.01235 -0.0384 0.0182 1.0000
7.750 1.0339 0.02189 0.01426 -0.0376 0.0149 1.0000
8.000 1.0568 0.02297 0.01556 -0.0369 0.0129 1.0000
8.250 1.0792 0.02404 0.01678 -0.0364 0.0108 1.0000
8.500 1.0990 0.02567 0.01861 -0.0356 0.0097 1.0000
8.750 1.1138 0.02852 0.02171 -0.0344 0.0088 1.0000
9.000 1.1314 0.03066 0.02424 -0.0334 0.0085 1.0000
9.250 1.1464 0.03326 0.02721 -0.0322 0.0081 1.0000
9.500 1.1582 0.03632 0.03068 -0.0310 0.0078 1.0000
9.750 1.1658 0.03984 0.03464 -0.0298 0.0076 1.0000
10.000 1.1680 0.04377 0.03902 -0.0287 0.0074 1.0000
10.250 1.1640 0.04805 0.04372 -0.0277 0.0074 1.0000
10.500 1.1522 0.05239 0.04839 -0.0270 0.0073 1.0000
10.750 1.1356 0.05716 0.05342 -0.0280 0.0073 1.0000
11.000 1.1181 0.06361 0.06011 -0.0327 0.0074 1.0000
11.250 1.1006 0.07214 0.06884 -0.0404 0.0075 1.0000
11.500 1.0813 0.08243 0.07929 -0.0490 0.0076 1.0000
11.750 1.0589 0.09374 0.09070 -0.0568 0.0078 1.0000
12.000 1.0344 0.10536 0.10236 -0.0635 0.0080 1.0000
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