AG35 (ag35-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG35 (ag35-il) Reynolds number: 100,000 Max Cl/Cd: 51.61 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag35-il-100000-n5.txt Download as CSV file: xf-ag35-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3852 0.10383 0.09910 -0.0121 1.0000 0.0518
-11.000 -0.3897 0.09786 0.09313 -0.0142 1.0000 0.0395
-10.500 -0.4981 0.09911 0.09416 -0.0084 1.0000 0.0341
-10.250 -0.4952 0.09504 0.09013 -0.0100 1.0000 0.0328
-10.000 -0.4946 0.09053 0.08566 -0.0124 1.0000 0.0315
-9.500 -0.5068 0.07386 0.06908 -0.0296 1.0000 0.0273
-9.250 -0.5026 0.06864 0.06383 -0.0333 1.0000 0.0270
-9.000 -0.4977 0.06295 0.05806 -0.0370 1.0000 0.0268
-8.750 -0.4923 0.05678 0.05172 -0.0405 1.0000 0.0267
-8.500 -0.4863 0.05030 0.04489 -0.0434 1.0000 0.0270
-8.250 -0.4782 0.04481 0.03899 -0.0448 1.0000 0.0277
-8.000 -0.4645 0.04214 0.03622 -0.0447 1.0000 0.0287
-7.750 -0.4504 0.03843 0.03215 -0.0446 1.0000 0.0290
-7.500 -0.4350 0.03470 0.02795 -0.0441 1.0000 0.0292
-7.250 -0.4176 0.03171 0.02455 -0.0433 1.0000 0.0297
-7.000 -0.3986 0.02917 0.02161 -0.0424 1.0000 0.0303
-6.750 -0.3786 0.02700 0.01906 -0.0413 1.0000 0.0313
-6.500 -0.3576 0.02536 0.01705 -0.0403 1.0000 0.0336
-6.250 -0.3358 0.02384 0.01511 -0.0391 1.0000 0.0356
-6.000 -0.3139 0.02214 0.01319 -0.0381 1.0000 0.0369
-5.750 -0.2922 0.02088 0.01186 -0.0371 1.0000 0.0387
-5.500 -0.2700 0.01996 0.01086 -0.0362 1.0000 0.0415
-5.250 -0.2361 0.01907 0.00975 -0.0374 0.9953 0.0465
-5.000 -0.1998 0.01789 0.00858 -0.0393 0.9885 0.0515
-4.750 -0.1621 0.01708 0.00770 -0.0414 0.9818 0.0608
-4.500 -0.1259 0.01631 0.00691 -0.0432 0.9739 0.0738
-4.250 -0.0888 0.01555 0.00626 -0.0452 0.9666 0.1019
-4.000 -0.0532 0.01471 0.00579 -0.0470 0.9581 0.1753
-3.750 -0.0199 0.01394 0.00551 -0.0484 0.9483 0.3020
-3.500 0.0131 0.01314 0.00531 -0.0496 0.9387 0.4582
-3.250 0.0395 0.01221 0.00526 -0.0485 0.9278 0.6865
-3.000 0.0861 0.01168 0.00515 -0.0504 0.9192 0.9545
-2.750 0.1306 0.01159 0.00484 -0.0536 0.9067 1.0000
-2.500 0.1610 0.01158 0.00464 -0.0539 0.8905 1.0000
-2.250 0.1900 0.01157 0.00445 -0.0538 0.8734 1.0000
-2.000 0.2180 0.01158 0.00429 -0.0535 0.8555 1.0000
-1.750 0.2450 0.01160 0.00416 -0.0530 0.8364 1.0000
-1.250 0.2980 0.01167 0.00393 -0.0517 0.7962 1.0000
-1.000 0.3241 0.01174 0.00387 -0.0510 0.7749 1.0000
-0.750 0.3502 0.01183 0.00382 -0.0503 0.7535 1.0000
-0.500 0.3762 0.01194 0.00381 -0.0496 0.7311 1.0000
-0.250 0.4021 0.01206 0.00381 -0.0490 0.7086 1.0000
0.000 0.4280 0.01220 0.00385 -0.0484 0.6846 1.0000
0.250 0.4539 0.01234 0.00390 -0.0479 0.6602 1.0000
0.500 0.4798 0.01249 0.00392 -0.0473 0.6374 1.0000
0.750 0.5056 0.01269 0.00395 -0.0466 0.6175 1.0000
1.000 0.5315 0.01292 0.00405 -0.0461 0.5989 1.0000
1.250 0.5575 0.01318 0.00423 -0.0457 0.5816 1.0000
1.500 0.5836 0.01346 0.00443 -0.0453 0.5654 1.0000
1.750 0.6097 0.01375 0.00465 -0.0449 0.5495 1.0000
2.000 0.6358 0.01403 0.00490 -0.0446 0.5337 1.0000
2.250 0.6619 0.01431 0.00518 -0.0442 0.5175 1.0000
2.500 0.6879 0.01458 0.00547 -0.0439 0.5005 1.0000
2.750 0.7138 0.01484 0.00576 -0.0436 0.4827 1.0000
3.000 0.7395 0.01510 0.00605 -0.0433 0.4637 1.0000
3.250 0.7651 0.01537 0.00636 -0.0429 0.4434 1.0000
3.500 0.7903 0.01564 0.00666 -0.0425 0.4205 1.0000
3.750 0.8153 0.01595 0.00698 -0.0420 0.3957 1.0000
4.000 0.8398 0.01632 0.00734 -0.0416 0.3691 1.0000
4.250 0.8639 0.01674 0.00773 -0.0411 0.3414 1.0000
4.500 0.8876 0.01724 0.00818 -0.0406 0.3135 1.0000
4.750 0.9109 0.01780 0.00869 -0.0401 0.2868 1.0000
5.000 0.9339 0.01841 0.00929 -0.0396 0.2607 1.0000
5.250 0.9567 0.01905 0.00993 -0.0390 0.2364 1.0000
5.500 0.9790 0.01976 0.01061 -0.0385 0.2137 1.0000
5.750 1.0008 0.02050 0.01135 -0.0379 0.1913 1.0000
6.000 1.0224 0.02127 0.01215 -0.0373 0.1700 1.0000
6.250 1.0432 0.02212 0.01302 -0.0367 0.1487 1.0000
6.500 1.0637 0.02300 0.01392 -0.0360 0.1278 1.0000
6.750 1.0829 0.02400 0.01490 -0.0353 0.1083 1.0000
7.000 1.1016 0.02507 0.01599 -0.0345 0.0905 1.0000
7.250 1.1190 0.02626 0.01720 -0.0335 0.0747 1.0000
7.500 1.1350 0.02759 0.01859 -0.0324 0.0620 1.0000
7.750 1.1494 0.02905 0.02011 -0.0312 0.0524 1.0000
8.000 1.1617 0.03064 0.02174 -0.0298 0.0451 1.0000
8.250 1.1740 0.03219 0.02345 -0.0283 0.0397 1.0000
8.500 1.1819 0.03405 0.02536 -0.0265 0.0361 1.0000
8.750 1.1918 0.03571 0.02724 -0.0249 0.0325 1.0000
9.000 1.1979 0.03743 0.02907 -0.0231 0.0300 1.0000
9.250 1.1987 0.03956 0.03131 -0.0209 0.0285 1.0000
9.500 1.2021 0.04179 0.03373 -0.0191 0.0273 1.0000
9.750 1.2053 0.04412 0.03630 -0.0175 0.0260 1.0000
10.000 1.2069 0.04660 0.03899 -0.0163 0.0247 1.0000
10.250 1.2069 0.04921 0.04178 -0.0156 0.0236 1.0000
10.500 1.2053 0.05204 0.04474 -0.0152 0.0226 1.0000
10.750 1.2022 0.05522 0.04803 -0.0152 0.0218 1.0000
11.000 1.1970 0.05894 0.05185 -0.0154 0.0212 1.0000
11.250 1.1910 0.06299 0.05619 -0.0160 0.0208 1.0000
11.500 1.1828 0.06757 0.06103 -0.0172 0.0205 1.0000
11.750 1.1722 0.07271 0.06643 -0.0190 0.0203 1.0000
12.000 1.1594 0.07843 0.07239 -0.0215 0.0202 1.0000
12.250 1.1444 0.08473 0.07892 -0.0245 0.0201 1.0000
12.500 1.1274 0.09168 0.08608 -0.0281 0.0201 1.0000
12.750 1.1087 0.09928 0.09388 -0.0323 0.0202 1.0000
13.000 1.0886 0.10767 0.10245 -0.0371 0.0203 1.0000
13.250 1.0675 0.11692 0.11185 -0.0425 0.0205 1.0000
13.500 1.0453 0.12705 0.12211 -0.0483 0.0207 1.0000
13.750 1.0226 0.13810 0.13326 -0.0546 0.0210 1.0000
14.000 1.0002 0.14992 0.14513 -0.0610 0.0212 1.0000
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