AG38 (ag38-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG38 (ag38-il) Reynolds number: 200,000 Max Cl/Cd: 63.99 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag38-il-200000.txt Download as CSV file: xf-ag38-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG38
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5303 0.10789 0.10432 -0.0058 1.0000 0.0331
-9.750 -0.5274 0.10403 0.10049 -0.0088 1.0000 0.0332
-9.500 -0.5282 0.09764 0.09415 -0.0081 1.0000 0.0339
-9.250 -0.5206 0.09420 0.09069 -0.0064 1.0000 0.0348
-9.000 -0.5152 0.09094 0.08745 -0.0067 1.0000 0.0355
-8.750 -0.5117 0.08757 0.08411 -0.0081 1.0000 0.0363
-8.500 -0.5069 0.08383 0.08040 -0.0108 1.0000 0.0373
-8.250 -0.4997 0.07969 0.07628 -0.0147 1.0000 0.0384
-8.000 -0.4907 0.07523 0.07181 -0.0192 1.0000 0.0397
-7.750 -0.4788 0.07033 0.06686 -0.0246 1.0000 0.0415
-7.500 -0.4553 0.06454 0.06072 -0.0350 1.0000 0.0442
-7.250 -0.4446 0.05883 0.05478 -0.0377 1.0000 0.0448
-7.000 -0.4368 0.05403 0.05013 -0.0370 1.0000 0.0462
-6.750 -0.4234 0.05141 0.04753 -0.0364 1.0000 0.0479
-6.500 -0.4070 0.04834 0.04436 -0.0369 1.0000 0.0507
-6.250 -0.3827 0.04377 0.03906 -0.0396 1.0000 0.0580
-6.000 -0.3685 0.04067 0.03620 -0.0389 1.0000 0.0607
-5.750 -0.3487 0.03833 0.03374 -0.0386 1.0000 0.0658
-5.500 -0.3264 0.03478 0.02978 -0.0391 1.0000 0.0734
-5.250 -0.3060 0.03261 0.02759 -0.0386 1.0000 0.0776
-5.000 -0.2832 0.03008 0.02473 -0.0385 1.0000 0.0880
-4.750 -0.2602 0.02826 0.02264 -0.0381 1.0000 0.1009
-4.500 -0.2220 0.02061 0.01372 -0.0359 1.0000 0.0407
-4.250 -0.1960 0.01860 0.01136 -0.0350 1.0000 0.0401
-4.000 -0.1703 0.01746 0.00997 -0.0342 1.0000 0.0423
-3.750 -0.1440 0.01607 0.00837 -0.0334 1.0000 0.0427
-3.500 -0.1178 0.01507 0.00724 -0.0327 1.0000 0.0439
-3.250 -0.0909 0.01369 0.00588 -0.0324 1.0000 0.0478
-3.000 -0.0649 0.01312 0.00532 -0.0320 1.0000 0.0545
-2.750 -0.0378 0.01233 0.00456 -0.0318 1.0000 0.0627
-2.500 -0.0101 0.01171 0.00405 -0.0319 1.0000 0.0895
-2.250 0.0163 0.00865 0.00393 -0.0317 1.0000 0.8215
-2.000 0.0434 0.00852 0.00384 -0.0312 1.0000 1.0000
-1.750 0.0683 0.00866 0.00384 -0.0308 1.0000 1.0000
-1.500 0.0941 0.00883 0.00390 -0.0308 0.9996 1.0000
-1.250 0.1434 0.00884 0.00377 -0.0354 0.9904 1.0000
-1.000 0.1927 0.00879 0.00364 -0.0399 0.9803 1.0000
-0.750 0.2432 0.00868 0.00347 -0.0446 0.9702 1.0000
-0.500 0.2885 0.00853 0.00328 -0.0480 0.9562 1.0000
-0.250 0.3255 0.00838 0.00310 -0.0495 0.9345 1.0000
0.000 0.3589 0.00824 0.00293 -0.0502 0.9063 1.0000
0.250 0.3888 0.00811 0.00273 -0.0498 0.8657 1.0000
0.500 0.4175 0.00808 0.00253 -0.0491 0.8241 1.0000
0.750 0.4428 0.00827 0.00251 -0.0480 0.7803 1.0000
1.000 0.4679 0.00853 0.00258 -0.0470 0.7389 1.0000
1.250 0.4933 0.00877 0.00266 -0.0462 0.6996 1.0000
1.500 0.5190 0.00901 0.00274 -0.0456 0.6609 1.0000
1.750 0.5445 0.00930 0.00284 -0.0450 0.6280 1.0000
2.000 0.5703 0.00964 0.00302 -0.0444 0.5991 1.0000
2.250 0.5963 0.00996 0.00322 -0.0440 0.5714 1.0000
2.500 0.6225 0.01026 0.00344 -0.0437 0.5442 1.0000
2.750 0.6486 0.01055 0.00365 -0.0433 0.5160 1.0000
3.000 0.6747 0.01081 0.00388 -0.0430 0.4857 1.0000
3.250 0.7007 0.01106 0.00407 -0.0426 0.4504 1.0000
3.500 0.7263 0.01135 0.00426 -0.0422 0.4084 1.0000
3.750 0.7514 0.01176 0.00450 -0.0418 0.3623 1.0000
4.000 0.7761 0.01226 0.00485 -0.0415 0.3158 1.0000
4.250 0.8007 0.01283 0.00523 -0.0411 0.2708 1.0000
4.500 0.8251 0.01346 0.00568 -0.0408 0.2272 1.0000
4.750 0.8491 0.01417 0.00620 -0.0405 0.1844 1.0000
5.000 0.8725 0.01501 0.00686 -0.0401 0.1427 1.0000
5.250 0.8957 0.01595 0.00766 -0.0395 0.1099 1.0000
5.500 0.9178 0.01705 0.00860 -0.0389 0.0889 1.0000
5.750 0.9401 0.01812 0.00964 -0.0381 0.0759 1.0000
6.000 0.9635 0.01901 0.01062 -0.0375 0.0671 1.0000
6.250 0.9853 0.02022 0.01189 -0.0367 0.0603 1.0000
6.500 1.0078 0.02126 0.01296 -0.0360 0.0549 1.0000
6.750 1.0286 0.02316 0.01490 -0.0350 0.0512 1.0000
7.000 1.0518 0.02432 0.01625 -0.0343 0.0479 1.0000
7.250 1.0740 0.02545 0.01749 -0.0337 0.0444 1.0000
7.500 1.0943 0.02787 0.01998 -0.0329 0.0418 1.0000
7.750 1.1143 0.03037 0.02281 -0.0319 0.0404 1.0000
8.000 1.1340 0.03217 0.02496 -0.0307 0.0387 1.0000
8.250 1.1520 0.03403 0.02713 -0.0296 0.0365 1.0000
8.500 1.1683 0.03632 0.02970 -0.0284 0.0350 1.0000
8.750 1.1817 0.03898 0.03269 -0.0269 0.0340 1.0000
9.000 1.1917 0.04204 0.03606 -0.0254 0.0333 1.0000
9.250 1.1980 0.04555 0.03985 -0.0237 0.0325 1.0000
9.500 1.1949 0.05044 0.04510 -0.0217 0.0318 1.0000
9.750 1.1830 0.05581 0.05087 -0.0193 0.0315 1.0000
10.000 1.1667 0.06070 0.05609 -0.0170 0.0314 1.0000
10.250 1.1474 0.06452 0.06016 -0.0143 0.0314 1.0000
10.500 1.1279 0.06842 0.06426 -0.0131 0.0314 1.0000
10.750 1.1096 0.07275 0.06878 -0.0139 0.0315 1.0000
11.000 1.0914 0.07788 0.07410 -0.0166 0.0316 1.0000
11.250 1.0720 0.08440 0.08082 -0.0220 0.0320 1.0000
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Polar data table (+)
Polar graphs
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