AG45ct -02f (ag45ct02r-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG45ct -02f (ag45ct02r-il) Reynolds number: 50,000 Max Cl/Cd: 34.32 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag45ct02r-il-50000-n5.txt Download as CSV file: xf-ag45ct02r-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG45ct -02f
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5532 0.10629 0.09970 0.0151 1.0000 0.1005
-8.000 -0.5498 0.10242 0.09588 0.0129 1.0000 0.1002
-7.750 -0.5500 0.09357 0.08702 0.0005 1.0000 0.0522
-7.500 -0.5405 0.08977 0.08325 0.0024 1.0000 0.0493
-7.250 -0.5333 0.08505 0.07856 -0.0011 1.0000 0.0470
-6.750 -0.5112 0.07089 0.06417 -0.0179 1.0000 0.0400
-6.500 -0.4992 0.06650 0.05974 -0.0196 1.0000 0.0394
-6.250 -0.4852 0.06163 0.05475 -0.0224 1.0000 0.0390
-6.000 -0.4691 0.05657 0.04945 -0.0255 1.0000 0.0390
-5.750 -0.4507 0.05156 0.04408 -0.0282 1.0000 0.0394
-5.500 -0.4299 0.04697 0.03897 -0.0302 1.0000 0.0400
-5.250 -0.4086 0.04272 0.03430 -0.0315 1.0000 0.0406
-5.000 -0.3864 0.03891 0.03010 -0.0322 1.0000 0.0412
-4.750 -0.3623 0.03545 0.02620 -0.0326 1.0000 0.0415
-4.500 -0.3374 0.03244 0.02277 -0.0326 1.0000 0.0424
-4.250 -0.3116 0.02984 0.01979 -0.0325 1.0000 0.0439
-4.000 -0.2854 0.02779 0.01740 -0.0321 1.0000 0.0482
-3.750 -0.2579 0.02583 0.01493 -0.0315 1.0000 0.0530
-3.500 -0.2324 0.02391 0.01291 -0.0309 1.0000 0.0574
-3.250 -0.2060 0.02246 0.01122 -0.0301 1.0000 0.0667
-3.000 -0.1798 0.02110 0.00976 -0.0294 1.0000 0.0797
-2.750 -0.1536 0.01984 0.00853 -0.0290 1.0000 0.1062
-2.500 -0.1277 0.01836 0.00744 -0.0289 1.0000 0.1681
-2.250 -0.1042 0.01657 0.00668 -0.0287 1.0000 0.3597
-2.000 -0.0911 0.01485 0.00647 -0.0246 1.0000 0.6912
-1.750 -0.0457 0.01413 0.00580 -0.0265 1.0000 1.0000
-1.500 -0.0214 0.01412 0.00543 -0.0260 1.0000 1.0000
-1.250 0.0024 0.01413 0.00514 -0.0256 1.0000 1.0000
-1.000 0.0257 0.01417 0.00496 -0.0251 1.0000 1.0000
-0.750 0.0484 0.01426 0.00486 -0.0247 1.0000 1.0000
-0.500 0.0704 0.01440 0.00485 -0.0243 1.0000 1.0000
-0.250 0.1050 0.01461 0.00487 -0.0264 0.9862 1.0000
0.000 0.1532 0.01479 0.00488 -0.0308 0.9572 1.0000
0.500 0.2392 0.01510 0.00492 -0.0367 0.8952 1.0000
0.750 0.2764 0.01526 0.00496 -0.0381 0.8637 1.0000
1.000 0.3091 0.01544 0.00502 -0.0385 0.8332 1.0000
1.250 0.3383 0.01566 0.00511 -0.0381 0.8041 1.0000
1.500 0.3651 0.01592 0.00525 -0.0373 0.7763 1.0000
1.750 0.3908 0.01621 0.00542 -0.0362 0.7498 1.0000
2.000 0.4160 0.01653 0.00563 -0.0351 0.7244 1.0000
2.250 0.4410 0.01688 0.00588 -0.0340 0.6996 1.0000
2.500 0.4659 0.01722 0.00623 -0.0330 0.6725 1.0000
2.750 0.4907 0.01753 0.00651 -0.0321 0.6459 1.0000
3.000 0.5155 0.01783 0.00678 -0.0310 0.6194 1.0000
3.250 0.5402 0.01812 0.00704 -0.0300 0.5925 1.0000
3.500 0.5650 0.01842 0.00733 -0.0290 0.5650 1.0000
3.750 0.5897 0.01875 0.00769 -0.0281 0.5369 1.0000
4.000 0.6144 0.01911 0.00803 -0.0271 0.5086 1.0000
4.250 0.6390 0.01950 0.00841 -0.0262 0.4799 1.0000
4.500 0.6639 0.01994 0.00885 -0.0255 0.4507 1.0000
4.750 0.6887 0.02043 0.00940 -0.0247 0.4213 1.0000
5.000 0.7134 0.02097 0.00996 -0.0241 0.3921 1.0000
5.250 0.7378 0.02155 0.01057 -0.0234 0.3631 1.0000
5.500 0.7619 0.02220 0.01125 -0.0227 0.3344 1.0000
5.750 0.7858 0.02292 0.01205 -0.0221 0.3062 1.0000
6.000 0.8093 0.02370 0.01288 -0.0214 0.2782 1.0000
6.250 0.8325 0.02456 0.01379 -0.0208 0.2514 1.0000
6.500 0.8551 0.02550 0.01478 -0.0201 0.2254 1.0000
6.750 0.8772 0.02653 0.01582 -0.0195 0.2007 1.0000
7.000 0.8990 0.02769 0.01714 -0.0189 0.1766 1.0000
7.250 0.9203 0.02899 0.01856 -0.0182 0.1547 1.0000
7.500 0.9402 0.03037 0.01995 -0.0176 0.1345 1.0000
7.750 0.9604 0.03204 0.02178 -0.0168 0.1171 1.0000
8.000 0.9792 0.03375 0.02367 -0.0161 0.1003 1.0000
8.250 0.9977 0.03583 0.02593 -0.0152 0.0885 1.0000
8.500 1.0147 0.03790 0.02816 -0.0145 0.0774 1.0000
8.750 1.0310 0.04007 0.03047 -0.0137 0.0694 1.0000
9.000 1.0460 0.04317 0.03410 -0.0127 0.0628 1.0000
9.250 1.0592 0.04537 0.03624 -0.0121 0.0568 1.0000
9.500 1.0677 0.04927 0.04083 -0.0113 0.0528 1.0000
9.750 1.0729 0.05329 0.04531 -0.0107 0.0503 1.0000
10.000 1.0758 0.05683 0.04913 -0.0103 0.0479 1.0000
10.250 1.0802 0.05983 0.05210 -0.0099 0.0453 1.0000
10.500 1.0675 0.06468 0.05740 -0.0103 0.0446 1.0000
10.750 1.0504 0.06968 0.06269 -0.0115 0.0444 1.0000
11.000 1.0321 0.07562 0.06883 -0.0149 0.0445 1.0000
11.250 1.0138 0.08243 0.07578 -0.0195 0.0449 1.0000
11.500 0.9957 0.08999 0.08344 -0.0247 0.0453 1.0000
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Polar data table (+)
Polar graphs
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