AG12 (ag12-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AG12 (ag12-il) Reynolds number: 100,000 Max Cl/Cd: 47.12 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag12-il-100000.txt Download as CSV file: xf-ag12-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5656 0.11248 0.10765 0.0179 1.0000 0.0736
-8.500 -0.5699 0.10995 0.10520 0.0122 1.0000 0.0753
-8.250 -0.5740 0.10717 0.10252 0.0054 1.0000 0.0758
-8.000 -0.5521 0.10114 0.09644 0.0136 1.0000 0.0812
-7.750 -0.5479 0.09774 0.09308 0.0116 1.0000 0.0852
-7.500 -0.5500 0.09451 0.08995 0.0020 1.0000 0.0885
-7.250 -0.5433 0.08919 0.08468 -0.0030 1.0000 0.0903
-7.000 -0.5316 0.08584 0.08134 0.0025 1.0000 0.0939
-6.750 -0.5205 0.08175 0.07726 -0.0025 1.0000 0.0995
-6.500 -0.5073 0.07571 0.07122 -0.0136 1.0000 0.1042
-6.250 -0.4951 0.07266 0.06819 -0.0107 1.0000 0.1086
-6.000 -0.4756 0.06657 0.06200 -0.0217 1.0000 0.1179
-5.750 -0.4611 0.06349 0.05896 -0.0199 1.0000 0.1232
-5.500 -0.4315 0.05816 0.05316 -0.0337 1.0000 0.1434
-5.250 -0.4187 0.05400 0.04924 -0.0301 1.0000 0.1460
-5.000 -0.3965 0.05001 0.04514 -0.0329 1.0000 0.1595
-4.750 -0.3406 0.03290 0.02622 -0.0452 1.0000 0.0602
-4.500 -0.3123 0.02823 0.02097 -0.0460 1.0000 0.0550
-4.250 -0.2838 0.02520 0.01739 -0.0463 1.0000 0.0563
-4.000 -0.2551 0.02286 0.01447 -0.0461 1.0000 0.0601
-3.750 -0.2260 0.02058 0.01169 -0.0455 1.0000 0.0619
-3.500 -0.1988 0.01828 0.00931 -0.0451 1.0000 0.0675
-3.250 -0.1718 0.01691 0.00791 -0.0446 1.0000 0.0841
-3.000 -0.1448 0.01538 0.00646 -0.0441 1.0000 0.1135
-2.750 -0.1182 0.01377 0.00532 -0.0439 1.0000 0.1969
-2.500 -0.0929 0.01244 0.00478 -0.0437 1.0000 0.3567
-2.250 -0.0691 0.01167 0.00453 -0.0427 1.0000 0.5005
-2.000 -0.0471 0.01092 0.00430 -0.0409 1.0000 0.6413
-1.750 -0.0251 0.00977 0.00393 -0.0378 1.0000 1.0000
-1.500 0.0031 0.00978 0.00359 -0.0381 1.0000 1.0000
-1.250 0.0301 0.00980 0.00333 -0.0381 1.0000 1.0000
-1.000 0.0566 0.00983 0.00317 -0.0380 1.0000 1.0000
-0.750 0.0828 0.00989 0.00307 -0.0378 1.0000 1.0000
-0.500 0.1088 0.00996 0.00303 -0.0377 1.0000 1.0000
-0.250 0.1345 0.01006 0.00304 -0.0376 1.0000 1.0000
0.000 0.1600 0.01019 0.00308 -0.0375 1.0000 1.0000
0.250 0.1852 0.01037 0.00321 -0.0375 1.0000 1.0000
0.500 0.2102 0.01060 0.00341 -0.0376 1.0000 1.0000
0.750 0.2346 0.01091 0.00371 -0.0379 1.0000 1.0000
1.000 0.2812 0.01119 0.00402 -0.0426 0.9857 1.0000
1.250 0.3427 0.01126 0.00414 -0.0493 0.9598 1.0000
1.500 0.3942 0.01121 0.00417 -0.0534 0.9287 1.0000
1.750 0.4326 0.01119 0.00419 -0.0545 0.8901 1.0000
2.000 0.4620 0.01124 0.00420 -0.0534 0.8481 1.0000
2.250 0.4867 0.01138 0.00425 -0.0515 0.8049 1.0000
2.500 0.5101 0.01161 0.00434 -0.0495 0.7607 1.0000
2.750 0.5335 0.01189 0.00454 -0.0477 0.7158 1.0000
3.000 0.5572 0.01222 0.00471 -0.0461 0.6714 1.0000
3.250 0.5813 0.01259 0.00492 -0.0446 0.6276 1.0000
3.500 0.6056 0.01300 0.00517 -0.0434 0.5843 1.0000
3.750 0.6301 0.01344 0.00546 -0.0423 0.5401 1.0000
4.000 0.6548 0.01391 0.00585 -0.0413 0.4958 1.0000
4.250 0.6794 0.01442 0.00623 -0.0404 0.4518 1.0000
4.500 0.7040 0.01498 0.00664 -0.0396 0.4080 1.0000
4.750 0.7284 0.01560 0.00710 -0.0388 0.3642 1.0000
5.000 0.7529 0.01628 0.00768 -0.0382 0.3195 1.0000
5.250 0.7771 0.01706 0.00839 -0.0375 0.2762 1.0000
5.500 0.8011 0.01794 0.00914 -0.0369 0.2347 1.0000
5.750 0.8249 0.01899 0.01005 -0.0362 0.1974 1.0000
6.000 0.8485 0.02013 0.01109 -0.0356 0.1633 1.0000
6.250 0.8718 0.02149 0.01233 -0.0349 0.1349 1.0000
6.500 0.8953 0.02299 0.01387 -0.0341 0.1107 1.0000
6.750 0.9182 0.02470 0.01561 -0.0334 0.0906 1.0000
7.000 0.9417 0.02692 0.01804 -0.0324 0.0766 1.0000
7.250 0.9640 0.02897 0.02027 -0.0316 0.0639 1.0000
7.500 0.9858 0.03216 0.02351 -0.0308 0.0568 1.0000
7.750 1.0063 0.03489 0.02693 -0.0295 0.0506 1.0000
8.000 1.0252 0.03769 0.02986 -0.0289 0.0457 1.0000
8.250 1.0373 0.04354 0.03621 -0.0279 0.0444 1.0000
8.500 1.0471 0.04832 0.04166 -0.0268 0.0440 1.0000
8.750 1.0520 0.05400 0.04787 -0.0260 0.0442 1.0000
9.000 1.0529 0.06008 0.05435 -0.0256 0.0444 1.0000
9.250 1.0509 0.06516 0.05987 -0.0253 0.0446 1.0000
9.500 1.0444 0.06988 0.06495 -0.0255 0.0448 1.0000
9.750 0.9785 0.08212 0.07788 -0.0350 0.0516 1.0000
10.000 0.9583 0.09166 0.08744 -0.0434 0.0532 1.0000
10.250 0.9481 0.09961 0.09537 -0.0481 0.0548 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG12 (ag12-il)