AG35 (ag35-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG35 (ag35-il) Reynolds number: 50,000 Max Cl/Cd: 36.88 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag35-il-50000-n5.txt Download as CSV file: xf-ag35-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG35
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4883 0.09167 0.08486 -0.0168 1.0000 0.0561
-9.500 -0.4869 0.08742 0.08067 -0.0192 1.0000 0.0547
-9.250 -0.4845 0.08256 0.07586 -0.0232 1.0000 0.0533
-9.000 -0.4815 0.07717 0.07048 -0.0277 1.0000 0.0519
-8.750 -0.4781 0.07112 0.06438 -0.0327 1.0000 0.0503
-8.500 -0.4740 0.06463 0.05774 -0.0374 1.0000 0.0490
-8.250 -0.4660 0.05982 0.05277 -0.0396 1.0000 0.0493
-8.000 -0.4553 0.05585 0.04864 -0.0409 1.0000 0.0504
-7.750 -0.4433 0.05174 0.04428 -0.0420 1.0000 0.0515
-7.500 -0.4297 0.04756 0.03975 -0.0428 1.0000 0.0523
-7.250 -0.4142 0.04352 0.03530 -0.0431 1.0000 0.0525
-7.000 -0.3968 0.03986 0.03115 -0.0430 1.0000 0.0529
-6.750 -0.3777 0.03661 0.02742 -0.0426 1.0000 0.0537
-6.500 -0.3571 0.03387 0.02416 -0.0419 1.0000 0.0561
-6.250 -0.3348 0.03151 0.02117 -0.0411 1.0000 0.0593
-6.000 -0.3137 0.02952 0.01908 -0.0403 1.0000 0.0622
-5.750 -0.2911 0.02778 0.01708 -0.0393 1.0000 0.0650
-5.500 -0.2679 0.02633 0.01527 -0.0383 1.0000 0.0706
-5.250 -0.2455 0.02500 0.01390 -0.0374 1.0000 0.0769
-5.000 -0.2220 0.02382 0.01252 -0.0363 1.0000 0.0838
-4.750 -0.1988 0.02283 0.01150 -0.0355 1.0000 0.0957
-4.500 -0.1753 0.02188 0.01048 -0.0347 1.0000 0.1101
-4.250 -0.1515 0.02099 0.00965 -0.0342 1.0000 0.1373
-4.000 -0.1274 0.01996 0.00895 -0.0339 1.0000 0.1949
-3.750 -0.1039 0.01884 0.00854 -0.0338 1.0000 0.3331
-3.500 -0.0853 0.01758 0.00839 -0.0321 1.0000 0.5550
-3.250 -0.0555 0.01656 0.00825 -0.0305 1.0000 1.0000
-3.000 -0.0246 0.01674 0.00802 -0.0318 0.9948 1.0000
-2.750 0.0206 0.01693 0.00780 -0.0357 0.9817 1.0000
-2.500 0.0652 0.01710 0.00763 -0.0394 0.9677 1.0000
-2.250 0.1096 0.01726 0.00752 -0.0430 0.9537 1.0000
-2.000 0.1539 0.01739 0.00742 -0.0464 0.9391 1.0000
-1.750 0.1950 0.01749 0.00735 -0.0491 0.9230 1.0000
-1.500 0.2335 0.01759 0.00730 -0.0511 0.9057 1.0000
-1.250 0.2704 0.01767 0.00726 -0.0527 0.8876 1.0000
-1.000 0.3059 0.01773 0.00722 -0.0539 0.8694 1.0000
-0.750 0.3377 0.01782 0.00722 -0.0543 0.8496 1.0000
-0.500 0.3677 0.01792 0.00725 -0.0544 0.8290 1.0000
-0.250 0.3981 0.01800 0.00725 -0.0543 0.8102 1.0000
0.000 0.4255 0.01814 0.00732 -0.0538 0.7896 1.0000
0.250 0.4529 0.01829 0.00740 -0.0533 0.7698 1.0000
0.500 0.4801 0.01843 0.00749 -0.0526 0.7509 1.0000
0.750 0.5053 0.01866 0.00768 -0.0518 0.7298 1.0000
1.000 0.5311 0.01885 0.00783 -0.0510 0.7100 1.0000
1.250 0.5564 0.01906 0.00804 -0.0502 0.6900 1.0000
1.500 0.5812 0.01930 0.00828 -0.0493 0.6686 1.0000
1.750 0.6064 0.01950 0.00844 -0.0484 0.6485 1.0000
2.000 0.6316 0.01972 0.00864 -0.0475 0.6283 1.0000
2.250 0.6574 0.01996 0.00886 -0.0467 0.6094 1.0000
2.500 0.6829 0.02028 0.00915 -0.0459 0.5898 1.0000
2.750 0.7080 0.02068 0.00956 -0.0452 0.5691 1.0000
3.000 0.7333 0.02109 0.00996 -0.0445 0.5490 1.0000
3.250 0.7578 0.02155 0.01052 -0.0438 0.5272 1.0000
3.500 0.7822 0.02200 0.01101 -0.0430 0.5055 1.0000
3.750 0.8058 0.02247 0.01158 -0.0422 0.4823 1.0000
4.000 0.8294 0.02290 0.01209 -0.0413 0.4588 1.0000
4.250 0.8522 0.02335 0.01268 -0.0404 0.4333 1.0000
4.500 0.8747 0.02381 0.01323 -0.0395 0.4068 1.0000
4.750 0.8968 0.02432 0.01379 -0.0385 0.3797 1.0000
5.000 0.9183 0.02490 0.01440 -0.0375 0.3522 1.0000
5.250 0.9394 0.02558 0.01512 -0.0365 0.3247 1.0000
5.500 0.9597 0.02637 0.01591 -0.0355 0.2979 1.0000
5.750 0.9795 0.02726 0.01678 -0.0345 0.2725 1.0000
6.000 0.9985 0.02827 0.01784 -0.0335 0.2470 1.0000
6.250 1.0168 0.02939 0.01904 -0.0325 0.2225 1.0000
6.500 1.0340 0.03061 0.02027 -0.0314 0.2001 1.0000
6.750 1.0501 0.03193 0.02166 -0.0303 0.1775 1.0000
7.000 1.0651 0.03337 0.02316 -0.0291 0.1569 1.0000
7.250 1.0786 0.03493 0.02479 -0.0279 0.1376 1.0000
7.500 1.0901 0.03659 0.02644 -0.0265 0.1210 1.0000
7.750 1.1008 0.03843 0.02836 -0.0251 0.1063 1.0000
8.000 1.1101 0.04038 0.03037 -0.0237 0.0938 1.0000
8.250 1.1187 0.04247 0.03263 -0.0222 0.0830 1.0000
8.500 1.1271 0.04480 0.03519 -0.0206 0.0743 1.0000
8.750 1.1329 0.04707 0.03746 -0.0191 0.0681 1.0000
9.000 1.1368 0.04962 0.04035 -0.0174 0.0623 1.0000
9.250 1.1407 0.05205 0.04280 -0.0160 0.0585 1.0000
9.500 1.1419 0.05522 0.04627 -0.0147 0.0552 1.0000
9.750 1.1386 0.05859 0.04998 -0.0137 0.0523 1.0000
10.000 1.1343 0.06195 0.05354 -0.0132 0.0499 1.0000
10.500 1.1290 0.06900 0.06078 -0.0130 0.0467 1.0000
10.750 1.1151 0.07422 0.06634 -0.0143 0.0462 1.0000
11.000 1.0986 0.08012 0.07253 -0.0165 0.0460 1.0000
11.250 1.0799 0.08680 0.07946 -0.0197 0.0459 1.0000
11.500 1.0595 0.09427 0.08709 -0.0237 0.0460 1.0000
11.750 1.0381 0.10249 0.09547 -0.0284 0.0463 1.0000
12.000 1.0162 0.11143 0.10454 -0.0335 0.0465 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG35 (ag35-il)