AG12 (ag12-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG12 (ag12-il) Reynolds number: 200,000 Max Cl/Cd: 58.69 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag12-il-200000-n5.txt Download as CSV file: xf-ag12-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG12
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5708 0.10468 0.10122 0.0174 1.0000 0.0154
-8.500 -0.5673 0.10092 0.09744 0.0167 1.0000 0.0140
-8.250 -0.5645 0.09671 0.09326 0.0147 1.0000 0.0130
-8.000 -0.5625 0.09213 0.08872 0.0121 1.0000 0.0122
-7.750 -0.5624 0.08667 0.08330 0.0084 1.0000 0.0113
-7.500 -0.5594 0.07903 0.07576 0.0014 1.0000 0.0101
-7.000 -0.5350 0.06790 0.06461 -0.0109 1.0000 0.0097
-6.750 -0.5192 0.06044 0.05710 -0.0196 1.0000 0.0096
-6.500 -0.4992 0.05145 0.04795 -0.0289 1.0000 0.0095
-6.250 -0.4777 0.04172 0.03787 -0.0365 1.0000 0.0094
-6.000 -0.4547 0.03367 0.02920 -0.0413 1.0000 0.0094
-5.750 -0.4301 0.02785 0.02262 -0.0438 1.0000 0.0102
-5.500 -0.4059 0.02601 0.02053 -0.0447 1.0000 0.0116
-5.250 -0.3799 0.02371 0.01786 -0.0451 1.0000 0.0125
-5.000 -0.3528 0.02075 0.01436 -0.0453 1.0000 0.0127
-4.750 -0.3258 0.01857 0.01176 -0.0452 1.0000 0.0130
-4.500 -0.2987 0.01685 0.00975 -0.0450 1.0000 0.0135
-4.250 -0.2718 0.01545 0.00814 -0.0447 1.0000 0.0143
-4.000 -0.2449 0.01433 0.00685 -0.0443 1.0000 0.0155
-3.750 -0.2181 0.01325 0.00561 -0.0441 1.0000 0.0176
-3.500 -0.1914 0.01264 0.00497 -0.0439 1.0000 0.0227
-3.250 -0.1641 0.01189 0.00411 -0.0437 1.0000 0.0283
-3.000 -0.1372 0.01129 0.00356 -0.0435 1.0000 0.0446
-2.750 -0.1104 0.01076 0.00314 -0.0434 1.0000 0.0776
-2.500 -0.0838 0.01028 0.00283 -0.0433 1.0000 0.1282
-2.250 -0.0574 0.00984 0.00263 -0.0432 1.0000 0.1910
-2.000 -0.0309 0.00947 0.00248 -0.0431 1.0000 0.2583
-1.750 -0.0046 0.00916 0.00238 -0.0429 1.0000 0.3240
-1.500 0.0274 0.00885 0.00231 -0.0440 0.9940 0.3956
-1.250 0.0640 0.00853 0.00221 -0.0459 0.9783 0.4759
-1.000 0.0995 0.00821 0.00215 -0.0474 0.9585 0.5587
-0.750 0.1331 0.00782 0.00209 -0.0483 0.9338 0.6578
-0.500 0.1603 0.00729 0.00201 -0.0473 0.9040 0.8136
-0.250 0.1968 0.00707 0.00183 -0.0482 0.8689 1.0000
0.000 0.2245 0.00717 0.00174 -0.0477 0.8310 1.0000
0.250 0.2506 0.00731 0.00168 -0.0469 0.7927 1.0000
0.500 0.2765 0.00747 0.00165 -0.0461 0.7547 1.0000
0.750 0.3025 0.00767 0.00164 -0.0453 0.7170 1.0000
1.000 0.3287 0.00788 0.00164 -0.0447 0.6798 1.0000
1.250 0.3550 0.00809 0.00167 -0.0441 0.6428 1.0000
1.500 0.3815 0.00832 0.00172 -0.0437 0.6069 1.0000
1.750 0.4081 0.00856 0.00181 -0.0433 0.5719 1.0000
2.000 0.4348 0.00880 0.00189 -0.0429 0.5375 1.0000
2.250 0.4615 0.00906 0.00200 -0.0426 0.5037 1.0000
2.500 0.4883 0.00932 0.00212 -0.0423 0.4707 1.0000
2.750 0.5151 0.00959 0.00227 -0.0420 0.4383 1.0000
3.000 0.5418 0.00988 0.00248 -0.0418 0.4063 1.0000
3.250 0.5686 0.01018 0.00267 -0.0415 0.3747 1.0000
3.500 0.5953 0.01049 0.00288 -0.0413 0.3434 1.0000
3.750 0.6220 0.01083 0.00312 -0.0411 0.3120 1.0000
4.000 0.6485 0.01119 0.00342 -0.0409 0.2811 1.0000
4.250 0.6750 0.01156 0.00372 -0.0407 0.2508 1.0000
4.500 0.7015 0.01196 0.00405 -0.0405 0.2216 1.0000
4.750 0.7277 0.01240 0.00441 -0.0403 0.1927 1.0000
5.000 0.7539 0.01285 0.00481 -0.0401 0.1666 1.0000
5.250 0.7799 0.01335 0.00529 -0.0399 0.1409 1.0000
5.500 0.8057 0.01388 0.00578 -0.0397 0.1184 1.0000
5.750 0.8314 0.01445 0.00631 -0.0394 0.0969 1.0000
6.000 0.8569 0.01506 0.00690 -0.0391 0.0785 1.0000
6.250 0.8822 0.01570 0.00755 -0.0388 0.0622 1.0000
6.500 0.9072 0.01641 0.00828 -0.0385 0.0488 1.0000
6.750 0.9320 0.01719 0.00915 -0.0381 0.0377 1.0000
7.000 0.9562 0.01809 0.01011 -0.0377 0.0292 1.0000
7.250 0.9795 0.01917 0.01124 -0.0372 0.0222 1.0000
7.500 1.0034 0.02010 0.01234 -0.0367 0.0179 1.0000
7.750 1.0243 0.02172 0.01409 -0.0359 0.0148 1.0000
8.000 1.0466 0.02295 0.01553 -0.0352 0.0128 1.0000
8.250 1.0690 0.02401 0.01674 -0.0347 0.0107 1.0000
8.500 1.0894 0.02550 0.01841 -0.0340 0.0096 1.0000
8.750 1.1055 0.02793 0.02113 -0.0329 0.0088 1.0000
9.000 1.1216 0.03041 0.02391 -0.0318 0.0083 1.0000
9.250 1.1371 0.03286 0.02671 -0.0307 0.0080 1.0000
9.500 1.1496 0.03575 0.03000 -0.0295 0.0077 1.0000
9.750 1.1582 0.03909 0.03375 -0.0283 0.0075 1.0000
10.000 1.1618 0.04283 0.03792 -0.0272 0.0073 1.0000
10.250 1.1593 0.04692 0.04242 -0.0262 0.0072 1.0000
10.500 1.1494 0.05113 0.04698 -0.0254 0.0072 1.0000
10.750 1.1338 0.05564 0.05176 -0.0259 0.0072 1.0000
11.000 1.1170 0.06158 0.05794 -0.0298 0.0072 1.0000
11.250 1.0999 0.06938 0.06596 -0.0366 0.0073 1.0000
11.500 1.0813 0.07893 0.07568 -0.0447 0.0074 1.0000
11.750 1.0606 0.08953 0.08640 -0.0525 0.0075 1.0000
12.000 1.0373 0.10075 0.09769 -0.0595 0.0077 1.0000
12.250 1.0125 0.11234 0.10931 -0.0657 0.0080 1.0000
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Polar data table (+)
Polar graphs
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