AG18 (ag18-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG18 (ag18-il) Reynolds number: 50,000 Max Cl/Cd: 36.74 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag18-il-50000-n5.txt Download as CSV file: xf-ag18-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG18
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5491 0.12295 0.11600 0.0169 1.0000 0.0871
-9.000 -0.5518 0.12073 0.11387 0.0132 1.0000 0.0899
-8.750 -0.5549 0.11842 0.11165 0.0089 1.0000 0.0906
-8.500 -0.5493 0.11412 0.10743 0.0075 1.0000 0.0912
-8.250 -0.5364 0.10901 0.10231 0.0087 1.0000 0.0926
-8.000 -0.5288 0.10508 0.09842 0.0080 1.0000 0.0938
-7.750 -0.5230 0.10139 0.09478 0.0065 1.0000 0.0947
-7.500 -0.5183 0.09771 0.09116 0.0042 1.0000 0.0947
-7.250 -0.5067 0.08995 0.08333 -0.0039 1.0000 0.0493
-7.000 -0.4971 0.08573 0.07915 -0.0056 1.0000 0.0466
-6.750 -0.4863 0.08094 0.07438 -0.0099 1.0000 0.0441
-6.250 -0.4489 0.06723 0.06047 -0.0278 1.0000 0.0381
-6.000 -0.4311 0.06197 0.05509 -0.0320 1.0000 0.0380
-5.750 -0.4103 0.05651 0.04940 -0.0368 1.0000 0.0382
-5.500 -0.3891 0.05121 0.04385 -0.0407 1.0000 0.0389
-5.250 -0.3708 0.04807 0.04070 -0.0417 1.0000 0.0412
-5.000 -0.3448 0.04315 0.03536 -0.0450 1.0000 0.0413
-4.750 -0.3169 0.03836 0.03000 -0.0476 1.0000 0.0409
-4.500 -0.2890 0.03444 0.02553 -0.0492 1.0000 0.0412
-4.250 -0.2611 0.03117 0.02168 -0.0500 1.0000 0.0423
-4.000 -0.2331 0.02839 0.01840 -0.0503 1.0000 0.0443
-3.750 -0.2047 0.02623 0.01564 -0.0502 1.0000 0.0504
-3.500 -0.1784 0.02425 0.01351 -0.0499 1.0000 0.0563
-3.250 -0.1514 0.02246 0.01137 -0.0492 1.0000 0.0625
-3.000 -0.1252 0.02112 0.00990 -0.0487 1.0000 0.0781
-2.750 -0.0984 0.01972 0.00846 -0.0483 1.0000 0.0984
-2.500 -0.0707 0.01840 0.00724 -0.0483 1.0000 0.1501
-2.250 -0.0436 0.01701 0.00650 -0.0486 1.0000 0.2768
-2.000 -0.0198 0.01591 0.00613 -0.0479 1.0000 0.4599
-1.750 -0.0019 0.01482 0.00580 -0.0452 1.0000 0.6525
-1.500 0.0209 0.01390 0.00525 -0.0429 1.0000 1.0000
-1.250 0.0473 0.01393 0.00489 -0.0428 1.0000 1.0000
-1.000 0.0732 0.01398 0.00458 -0.0426 1.0000 1.0000
-0.750 0.0988 0.01406 0.00440 -0.0424 1.0000 1.0000
-0.500 0.1240 0.01416 0.00430 -0.0422 1.0000 1.0000
-0.250 0.1489 0.01428 0.00426 -0.0420 1.0000 1.0000
0.000 0.1736 0.01444 0.00426 -0.0418 1.0000 1.0000
0.250 0.1979 0.01463 0.00435 -0.0416 1.0000 1.0000
0.500 0.2220 0.01487 0.00451 -0.0415 1.0000 1.0000
0.750 0.2464 0.01515 0.00475 -0.0416 0.9996 1.0000
1.000 0.2962 0.01543 0.00500 -0.0464 0.9759 1.0000
1.250 0.3457 0.01564 0.00522 -0.0508 0.9519 1.0000
1.500 0.3908 0.01578 0.00540 -0.0540 0.9250 1.0000
1.750 0.4312 0.01589 0.00557 -0.0560 0.8943 1.0000
2.000 0.4679 0.01599 0.00575 -0.0569 0.8611 1.0000
2.250 0.4998 0.01611 0.00589 -0.0568 0.8243 1.0000
2.500 0.5287 0.01626 0.00603 -0.0559 0.7853 1.0000
2.750 0.5550 0.01646 0.00620 -0.0545 0.7440 1.0000
3.000 0.5798 0.01671 0.00646 -0.0529 0.7002 1.0000
3.250 0.6038 0.01703 0.00669 -0.0511 0.6545 1.0000
3.500 0.6275 0.01740 0.00697 -0.0495 0.6061 1.0000
3.750 0.6509 0.01785 0.00729 -0.0479 0.5573 1.0000
4.000 0.6743 0.01838 0.00769 -0.0466 0.5077 1.0000
4.250 0.6977 0.01899 0.00824 -0.0454 0.4599 1.0000
4.500 0.7212 0.01966 0.00881 -0.0443 0.4137 1.0000
4.750 0.7450 0.02041 0.00947 -0.0435 0.3701 1.0000
5.000 0.7691 0.02122 0.01022 -0.0428 0.3290 1.0000
5.250 0.7931 0.02210 0.01106 -0.0422 0.2902 1.0000
5.500 0.8168 0.02305 0.01206 -0.0416 0.2547 1.0000
5.750 0.8404 0.02408 0.01312 -0.0410 0.2214 1.0000
6.000 0.8636 0.02521 0.01426 -0.0403 0.1921 1.0000
6.250 0.8864 0.02642 0.01550 -0.0397 0.1646 1.0000
6.500 0.9092 0.02782 0.01700 -0.0390 0.1415 1.0000
6.750 0.9309 0.02927 0.01850 -0.0383 0.1204 1.0000
7.000 0.9531 0.03104 0.02047 -0.0374 0.1033 1.0000
7.250 0.9737 0.03273 0.02239 -0.0367 0.0868 1.0000
7.500 0.9948 0.03512 0.02506 -0.0356 0.0759 1.0000
7.750 1.0137 0.03726 0.02745 -0.0349 0.0640 1.0000
8.000 1.0319 0.04000 0.03031 -0.0339 0.0576 1.0000
8.250 1.0487 0.04351 0.03448 -0.0328 0.0515 1.0000
8.500 1.0624 0.04612 0.03719 -0.0322 0.0456 1.0000
8.750 1.0714 0.05071 0.04256 -0.0312 0.0425 1.0000
9.000 1.0755 0.05561 0.04802 -0.0305 0.0407 1.0000
9.250 1.0741 0.06065 0.05354 -0.0301 0.0397 1.0000
9.500 1.0672 0.06581 0.05908 -0.0302 0.0390 1.0000
9.750 1.0531 0.07134 0.06491 -0.0311 0.0389 1.0000
10.000 1.0301 0.07753 0.07132 -0.0334 0.0396 1.0000
10.250 1.0060 0.08544 0.07936 -0.0393 0.0406 1.0000
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Polar data table (+)
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