AG12 (ag12-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG12 (ag12-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.11 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag12-il-1000000-n5.txt Download as CSV file: xf-ag12-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5912 0.08915 0.08762 0.0156 1.0000 0.0031
-8.000 -0.5926 0.08405 0.08255 0.0122 1.0000 0.0030
-7.750 -0.5903 0.07840 0.07691 0.0068 1.0000 0.0029
-7.500 -0.5818 0.07102 0.06954 -0.0023 1.0000 0.0029
-7.250 -0.5844 0.02139 0.01830 -0.0451 1.0000 0.0026
-7.000 -0.5607 0.01731 0.01361 -0.0460 1.0000 0.0027
-6.750 -0.5349 0.01541 0.01138 -0.0462 1.0000 0.0029
-6.500 -0.5084 0.01425 0.01001 -0.0462 1.0000 0.0030
-6.250 -0.4817 0.01346 0.00908 -0.0461 1.0000 0.0031
-6.000 -0.4553 0.01174 0.00706 -0.0462 1.0000 0.0035
-5.750 -0.4283 0.01116 0.00640 -0.0461 1.0000 0.0038
-5.500 -0.4012 0.01068 0.00586 -0.0460 1.0000 0.0040
-5.250 -0.3741 0.01019 0.00527 -0.0458 1.0000 0.0042
-5.000 -0.3469 0.00970 0.00472 -0.0457 1.0000 0.0045
-4.750 -0.3197 0.00923 0.00417 -0.0455 1.0000 0.0047
-4.500 -0.2925 0.00881 0.00369 -0.0453 1.0000 0.0050
-4.250 -0.2652 0.00851 0.00335 -0.0451 0.9998 0.0054
-4.000 -0.2317 0.00823 0.00303 -0.0463 0.9916 0.0057
-3.750 -0.1977 0.00768 0.00235 -0.0476 0.9792 0.0067
-3.500 -0.1639 0.00738 0.00202 -0.0487 0.9589 0.0083
-3.250 -0.1346 0.00722 0.00178 -0.0488 0.9260 0.0098
-3.000 -0.1092 0.00710 0.00155 -0.0479 0.8864 0.0146
-2.750 -0.0832 0.00704 0.00137 -0.0473 0.8483 0.0227
-2.500 -0.0567 0.00695 0.00120 -0.0468 0.8115 0.0390
-2.250 -0.0297 0.00688 0.00107 -0.0466 0.7766 0.0596
-2.000 -0.0024 0.00678 0.00095 -0.0464 0.7425 0.0893
-1.750 0.0251 0.00670 0.00085 -0.0462 0.7084 0.1223
-1.500 0.0527 0.00662 0.00076 -0.0462 0.6770 0.1607
-1.250 0.0804 0.00655 0.00070 -0.0461 0.6462 0.2010
-1.000 0.1081 0.00651 0.00065 -0.0461 0.6154 0.2375
-0.750 0.1359 0.00648 0.00062 -0.0460 0.5852 0.2796
-0.500 0.1637 0.00646 0.00060 -0.0460 0.5557 0.3178
-0.250 0.1915 0.00644 0.00059 -0.0460 0.5268 0.3621
0.000 0.2193 0.00643 0.00060 -0.0460 0.4997 0.4016
0.250 0.2471 0.00643 0.00062 -0.0460 0.4735 0.4435
0.500 0.2749 0.00643 0.00065 -0.0459 0.4466 0.4899
0.750 0.3026 0.00642 0.00069 -0.0459 0.4205 0.5412
1.000 0.3302 0.00639 0.00074 -0.0459 0.3959 0.6010
1.250 0.3576 0.00632 0.00080 -0.0458 0.3721 0.6769
1.500 0.3840 0.00615 0.00087 -0.0455 0.3489 0.7861
1.750 0.4087 0.00582 0.00092 -0.0444 0.3261 1.0000
2.000 0.4366 0.00599 0.00099 -0.0444 0.3037 1.0000
2.250 0.4643 0.00617 0.00107 -0.0443 0.2805 1.0000
2.500 0.4920 0.00637 0.00116 -0.0443 0.2565 1.0000
2.750 0.5197 0.00655 0.00126 -0.0442 0.2351 1.0000
3.000 0.5473 0.00677 0.00139 -0.0441 0.2117 1.0000
3.250 0.5749 0.00697 0.00152 -0.0440 0.1922 1.0000
3.500 0.6023 0.00722 0.00166 -0.0440 0.1696 1.0000
3.750 0.6298 0.00743 0.00182 -0.0439 0.1524 1.0000
4.000 0.6571 0.00770 0.00201 -0.0438 0.1314 1.0000
4.250 0.6845 0.00793 0.00219 -0.0437 0.1164 1.0000
4.500 0.7117 0.00821 0.00239 -0.0436 0.0990 1.0000
4.750 0.7387 0.00850 0.00262 -0.0435 0.0829 1.0000
5.000 0.7657 0.00881 0.00286 -0.0433 0.0675 1.0000
5.250 0.7927 0.00910 0.00313 -0.0432 0.0562 1.0000
5.500 0.8196 0.00942 0.00341 -0.0430 0.0448 1.0000
5.750 0.8463 0.00977 0.00371 -0.0429 0.0346 1.0000
6.000 0.8729 0.01013 0.00403 -0.0427 0.0257 1.0000
6.250 0.8995 0.01049 0.00438 -0.0425 0.0190 1.0000
6.500 0.9259 0.01087 0.00477 -0.0423 0.0138 1.0000
6.750 0.9522 0.01126 0.00516 -0.0421 0.0106 1.0000
7.000 0.9785 0.01166 0.00558 -0.0419 0.0080 1.0000
7.250 1.0045 0.01209 0.00603 -0.0416 0.0062 1.0000
7.500 1.0302 0.01260 0.00658 -0.0413 0.0047 1.0000
7.750 1.0560 0.01305 0.00709 -0.0410 0.0041 1.0000
8.000 1.0815 0.01355 0.00765 -0.0407 0.0035 1.0000
8.250 1.1064 0.01418 0.00833 -0.0404 0.0029 1.0000
8.500 1.1307 0.01496 0.00925 -0.0399 0.0025 1.0000
8.750 1.1556 0.01552 0.00989 -0.0396 0.0024 1.0000
9.000 1.1799 0.01618 0.01065 -0.0392 0.0023 1.0000
9.250 1.2038 0.01691 0.01148 -0.0387 0.0022 1.0000
9.500 1.2272 0.01769 0.01238 -0.0382 0.0021 1.0000
9.750 1.2501 0.01853 0.01334 -0.0377 0.0020 1.0000
10.000 1.2726 0.01943 0.01436 -0.0372 0.0019 1.0000
10.250 1.2945 0.02037 0.01542 -0.0366 0.0018 1.0000
10.500 1.3158 0.02136 0.01656 -0.0360 0.0017 1.0000
10.750 1.3366 0.02238 0.01771 -0.0353 0.0016 1.0000
11.000 1.3567 0.02345 0.01891 -0.0347 0.0016 1.0000
11.250 1.3758 0.02461 0.02021 -0.0339 0.0015 1.0000
11.500 1.3935 0.02592 0.02166 -0.0331 0.0014 1.0000
11.750 1.4089 0.02748 0.02339 -0.0322 0.0013 1.0000
12.000 1.4202 0.02952 0.02564 -0.0310 0.0013 1.0000
12.250 1.4207 0.03275 0.02919 -0.0292 0.0012 1.0000
12.500 1.4154 0.03623 0.03296 -0.0275 0.0011 1.0000
12.750 1.4124 0.03854 0.03544 -0.0256 0.0011 1.0000
13.000 1.4026 0.04183 0.03891 -0.0251 0.0011 1.0000
13.250 1.3906 0.04668 0.04395 -0.0275 0.0011 1.0000
13.500 1.3725 0.05448 0.05196 -0.0339 0.0011 1.0000
13.750 1.3440 0.06594 0.06365 -0.0430 0.0011 1.0000
14.000 1.3080 0.07876 0.07664 -0.0512 0.0011 1.0000
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Polar data table (+)
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