AG44ct -02f (ag44ct02r-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG44ct -02f (ag44ct02r-il) Reynolds number: 500,000 Max Cl/Cd: 78.22 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag44ct02r-il-500000-n5.txt Download as CSV file: xf-ag44ct02r-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG44ct -02f
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5597 0.09832 0.09611 0.0142 1.0000 0.0075
-8.500 -0.5572 0.09436 0.09217 0.0122 1.0000 0.0071
-8.250 -0.5557 0.09002 0.08785 0.0098 1.0000 0.0067
-8.000 -0.5555 0.08520 0.08306 0.0067 1.0000 0.0064
-7.750 -0.5646 0.07516 0.07307 -0.0024 1.0000 0.0055
-7.500 -0.5565 0.06729 0.06518 -0.0114 1.0000 0.0053
-7.250 -0.5439 0.05989 0.05771 -0.0194 1.0000 0.0052
-7.000 -0.5320 0.05049 0.04814 -0.0275 1.0000 0.0052
-6.750 -0.5236 0.03607 0.03323 -0.0341 1.0000 0.0052
-6.500 -0.5158 0.02347 0.01944 -0.0358 1.0000 0.0054
-6.250 -0.4944 0.02078 0.01636 -0.0356 1.0000 0.0056
-6.000 -0.4710 0.01912 0.01442 -0.0352 1.0000 0.0058
-5.750 -0.4472 0.01766 0.01271 -0.0348 1.0000 0.0060
-5.500 -0.4229 0.01637 0.01119 -0.0342 1.0000 0.0063
-5.250 -0.3981 0.01554 0.01021 -0.0337 1.0000 0.0067
-5.000 -0.3733 0.01465 0.00917 -0.0331 1.0000 0.0073
-4.750 -0.3486 0.01365 0.00799 -0.0324 1.0000 0.0075
-4.500 -0.3158 0.01253 0.00668 -0.0335 0.9945 0.0077
-4.250 -0.2818 0.01163 0.00565 -0.0348 0.9844 0.0078
-4.000 -0.2470 0.01090 0.00481 -0.0362 0.9696 0.0081
-3.750 -0.2121 0.01009 0.00389 -0.0377 0.9447 0.0087
-3.500 -0.1794 0.00966 0.00334 -0.0384 0.9004 0.0098
-3.250 -0.1542 0.00949 0.00292 -0.0374 0.8368 0.0111
-2.750 -0.1031 0.00924 0.00226 -0.0360 0.7552 0.0177
-2.500 -0.0762 0.00904 0.00200 -0.0356 0.7354 0.0285
-2.250 -0.0492 0.00884 0.00179 -0.0354 0.7209 0.0516
-2.000 -0.0222 0.00861 0.00164 -0.0352 0.7095 0.0903
-1.750 0.0051 0.00837 0.00152 -0.0351 0.6993 0.1405
-1.500 0.0324 0.00809 0.00142 -0.0351 0.6871 0.2016
-1.250 0.0596 0.00781 0.00132 -0.0350 0.6742 0.2758
-1.000 0.0866 0.00750 0.00124 -0.0349 0.6600 0.3632
-0.750 0.1134 0.00719 0.00118 -0.0347 0.6445 0.4622
-0.500 0.1398 0.00690 0.00113 -0.0345 0.6273 0.5601
-0.250 0.1656 0.00663 0.00111 -0.0340 0.6090 0.6604
0.000 0.1896 0.00632 0.00110 -0.0329 0.5898 0.7731
0.250 0.2114 0.00602 0.00111 -0.0310 0.5700 0.9036
0.500 0.2546 0.00605 0.00107 -0.0341 0.5442 0.9965
0.750 0.2825 0.00618 0.00106 -0.0341 0.5198 1.0000
1.000 0.3096 0.00632 0.00107 -0.0338 0.4954 1.0000
1.250 0.3367 0.00647 0.00109 -0.0336 0.4710 1.0000
1.500 0.3638 0.00663 0.00113 -0.0334 0.4469 1.0000
2.000 0.4180 0.00698 0.00124 -0.0330 0.3998 1.0000
2.250 0.4451 0.00716 0.00133 -0.0329 0.3779 1.0000
2.500 0.4723 0.00734 0.00142 -0.0327 0.3562 1.0000
2.750 0.4994 0.00754 0.00152 -0.0325 0.3359 1.0000
3.000 0.5265 0.00773 0.00163 -0.0324 0.3160 1.0000
3.500 0.5807 0.00813 0.00191 -0.0321 0.2797 1.0000
3.750 0.6077 0.00835 0.00206 -0.0319 0.2615 1.0000
4.000 0.6347 0.00857 0.00222 -0.0318 0.2445 1.0000
4.500 0.6885 0.00905 0.00261 -0.0315 0.2110 1.0000
4.750 0.7153 0.00930 0.00281 -0.0313 0.1947 1.0000
5.000 0.7420 0.00957 0.00304 -0.0312 0.1786 1.0000
5.250 0.7686 0.00986 0.00329 -0.0310 0.1623 1.0000
5.500 0.7950 0.01018 0.00356 -0.0308 0.1460 1.0000
5.750 0.8213 0.01050 0.00385 -0.0306 0.1305 1.0000
6.000 0.8475 0.01085 0.00415 -0.0304 0.1145 1.0000
6.250 0.8735 0.01123 0.00449 -0.0302 0.0989 1.0000
6.500 0.8994 0.01163 0.00486 -0.0300 0.0843 1.0000
6.750 0.9249 0.01208 0.00527 -0.0298 0.0695 1.0000
7.000 0.9502 0.01257 0.00571 -0.0295 0.0558 1.0000
7.250 0.9753 0.01307 0.00618 -0.0292 0.0439 1.0000
7.500 1.0003 0.01359 0.00668 -0.0289 0.0345 1.0000
7.750 1.0252 0.01413 0.00724 -0.0286 0.0270 1.0000
8.000 1.0499 0.01466 0.00781 -0.0283 0.0218 1.0000
8.250 1.0741 0.01530 0.00847 -0.0279 0.0173 1.0000
8.500 1.0986 0.01585 0.00909 -0.0275 0.0149 1.0000
8.750 1.1222 0.01654 0.00981 -0.0271 0.0123 1.0000
9.000 1.1456 0.01724 0.01060 -0.0266 0.0107 1.0000
9.250 1.1690 0.01791 0.01140 -0.0261 0.0096 1.0000
9.500 1.1916 0.01868 0.01225 -0.0256 0.0086 1.0000
9.750 1.2124 0.01972 0.01339 -0.0249 0.0076 1.0000
10.000 1.2335 0.02066 0.01447 -0.0243 0.0071 1.0000
10.250 1.2547 0.02151 0.01544 -0.0237 0.0065 1.0000
10.500 1.2754 0.02239 0.01643 -0.0231 0.0060 1.0000
10.750 1.2953 0.02332 0.01747 -0.0224 0.0055 1.0000
11.000 1.3131 0.02449 0.01878 -0.0216 0.0051 1.0000
11.250 1.3267 0.02613 0.02058 -0.0205 0.0048 1.0000
11.500 1.3401 0.02766 0.02228 -0.0193 0.0046 1.0000
11.750 1.3532 0.02910 0.02388 -0.0182 0.0044 1.0000
12.000 1.3635 0.03070 0.02567 -0.0170 0.0043 1.0000
12.250 1.3701 0.03245 0.02759 -0.0155 0.0041 1.0000
12.500 1.3712 0.03442 0.02973 -0.0137 0.0040 1.0000
12.750 1.3693 0.03685 0.03233 -0.0128 0.0039 1.0000
13.000 1.3652 0.04003 0.03569 -0.0132 0.0038 1.0000
13.250 1.3600 0.04401 0.03986 -0.0150 0.0037 1.0000
13.500 1.3526 0.04872 0.04475 -0.0175 0.0037 1.0000
13.750 1.3430 0.05411 0.05031 -0.0207 0.0036 1.0000
14.000 1.3294 0.06045 0.05683 -0.0245 0.0036 1.0000
14.250 1.3132 0.06746 0.06401 -0.0286 0.0036 1.0000
14.500 1.2938 0.07515 0.07185 -0.0329 0.0036 1.0000
14.750 1.2731 0.08315 0.08000 -0.0371 0.0036 1.0000
15.000 1.2509 0.09146 0.08844 -0.0414 0.0037 1.0000
15.250 1.2278 0.09999 0.09710 -0.0456 0.0037 1.0000
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Polar data table (+)
Polar graphs
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