AG16 (ag16-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG16 (ag16-il) Reynolds number: 50,000 Max Cl/Cd: 35.97 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag16-il-50000-n5.txt Download as CSV file: xf-ag16-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG16
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 -0.5440 0.09615 0.08944 0.0012 1.0000 0.0408
-8.000 -0.5420 0.09176 0.08512 -0.0015 1.0000 0.0406
-7.750 -0.5401 0.08724 0.08067 -0.0048 1.0000 0.0404
-7.500 -0.5351 0.08211 0.07561 -0.0096 1.0000 0.0403
-7.250 -0.5279 0.07641 0.06994 -0.0154 1.0000 0.0402
-7.000 -0.5183 0.06991 0.06342 -0.0223 1.0000 0.0400
-6.750 -0.5069 0.06293 0.05634 -0.0291 1.0000 0.0398
-6.500 -0.4936 0.05646 0.04965 -0.0349 1.0000 0.0399
-6.250 -0.4771 0.05038 0.04321 -0.0397 1.0000 0.0402
-6.000 -0.4575 0.04469 0.03703 -0.0433 1.0000 0.0405
-5.750 -0.4350 0.03968 0.03144 -0.0457 1.0000 0.0409
-5.500 -0.4105 0.03547 0.02653 -0.0471 1.0000 0.0420
-5.250 -0.3846 0.03193 0.02237 -0.0477 1.0000 0.0439
-5.000 -0.3581 0.02915 0.01900 -0.0478 1.0000 0.0486
-4.750 -0.3331 0.02721 0.01689 -0.0477 1.0000 0.0553
-4.500 -0.3066 0.02504 0.01430 -0.0470 1.0000 0.0609
-4.250 -0.2813 0.02346 0.01262 -0.0466 1.0000 0.0743
-4.000 -0.2558 0.02185 0.01101 -0.0462 1.0000 0.0918
-3.750 -0.2298 0.02048 0.00970 -0.0461 1.0000 0.1295
-3.500 -0.2033 0.01924 0.00863 -0.0462 1.0000 0.1925
-3.250 -0.1774 0.01835 0.00800 -0.0461 1.0000 0.2703
-3.000 -0.1521 0.01771 0.00752 -0.0457 1.0000 0.3461
-2.750 -0.1274 0.01719 0.00714 -0.0450 1.0000 0.4159
-2.500 -0.1034 0.01669 0.00680 -0.0441 1.0000 0.4817
-2.250 -0.0801 0.01621 0.00643 -0.0430 1.0000 0.5479
-2.000 -0.0582 0.01571 0.00613 -0.0414 1.0000 0.6183
-1.750 -0.0385 0.01516 0.00585 -0.0391 1.0000 0.7008
-1.500 -0.0194 0.01451 0.00553 -0.0362 1.0000 0.8318
-1.250 0.0109 0.01424 0.00513 -0.0370 1.0000 1.0000
-1.000 0.0371 0.01431 0.00489 -0.0372 1.0000 1.0000
-0.750 0.0626 0.01440 0.00477 -0.0373 1.0000 1.0000
-0.500 0.0876 0.01454 0.00473 -0.0373 1.0000 1.0000
-0.250 0.1121 0.01470 0.00476 -0.0373 1.0000 1.0000
0.000 0.1364 0.01492 0.00484 -0.0373 1.0000 1.0000
0.250 0.1624 0.01518 0.00502 -0.0378 0.9982 1.0000
0.500 0.2110 0.01545 0.00521 -0.0424 0.9774 1.0000
0.750 0.2596 0.01568 0.00541 -0.0468 0.9565 1.0000
1.000 0.3047 0.01585 0.00557 -0.0503 0.9331 1.0000
1.250 0.3466 0.01598 0.00572 -0.0528 0.9077 1.0000
1.500 0.3848 0.01609 0.00585 -0.0543 0.8799 1.0000
1.750 0.4193 0.01621 0.00602 -0.0550 0.8501 1.0000
2.000 0.4509 0.01634 0.00614 -0.0548 0.8191 1.0000
2.250 0.4795 0.01649 0.00628 -0.0541 0.7867 1.0000
2.500 0.5062 0.01669 0.00645 -0.0530 0.7529 1.0000
2.750 0.5321 0.01691 0.00669 -0.0517 0.7195 1.0000
3.000 0.5570 0.01719 0.00693 -0.0504 0.6841 1.0000
3.250 0.5818 0.01750 0.00719 -0.0490 0.6492 1.0000
3.500 0.6063 0.01785 0.00750 -0.0477 0.6131 1.0000
3.750 0.6308 0.01824 0.00792 -0.0465 0.5765 1.0000
4.000 0.6551 0.01867 0.00830 -0.0453 0.5400 1.0000
4.250 0.6793 0.01915 0.00876 -0.0442 0.5022 1.0000
4.500 0.7034 0.01967 0.00927 -0.0432 0.4641 1.0000
4.750 0.7277 0.02025 0.00983 -0.0423 0.4259 1.0000
5.000 0.7518 0.02090 0.01051 -0.0414 0.3877 1.0000
5.250 0.7757 0.02162 0.01121 -0.0406 0.3492 1.0000
5.500 0.7993 0.02240 0.01200 -0.0399 0.3103 1.0000
5.750 0.8225 0.02328 0.01288 -0.0392 0.2720 1.0000
6.000 0.8451 0.02428 0.01384 -0.0385 0.2347 1.0000
6.250 0.8671 0.02541 0.01494 -0.0378 0.1992 1.0000
6.500 0.8887 0.02669 0.01624 -0.0371 0.1644 1.0000
6.750 0.9096 0.02817 0.01779 -0.0364 0.1347 1.0000
7.000 0.9301 0.02989 0.01955 -0.0355 0.1105 1.0000
7.250 0.9493 0.03171 0.02131 -0.0347 0.0912 1.0000
7.500 0.9691 0.03381 0.02359 -0.0337 0.0767 1.0000
7.750 0.9876 0.03599 0.02589 -0.0327 0.0652 1.0000
8.000 1.0061 0.03829 0.02847 -0.0317 0.0559 1.0000
8.250 1.0242 0.04151 0.03205 -0.0305 0.0509 1.0000
8.500 1.0394 0.04424 0.03513 -0.0296 0.0450 1.0000
8.750 1.0514 0.04746 0.03858 -0.0287 0.0410 1.0000
9.000 1.0599 0.05184 0.04361 -0.0276 0.0391 1.0000
9.250 1.0626 0.05653 0.04894 -0.0268 0.0378 1.0000
9.500 1.0593 0.06136 0.05423 -0.0263 0.0370 1.0000
9.750 1.0500 0.06628 0.05952 -0.0263 0.0365 1.0000
10.000 1.0337 0.07131 0.06483 -0.0268 0.0365 1.0000
10.250 1.0131 0.07721 0.07093 -0.0294 0.0370 1.0000
10.500 0.9914 0.08455 0.07832 -0.0346 0.0378 1.0000
10.750 0.9706 0.09328 0.08713 -0.0414 0.0386 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG16 (ag16-il)