AG08 (ag08-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG08 (ag08-il) Reynolds number: 500,000 Max Cl/Cd: 71.96 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag08-il-500000-n5.txt Download as CSV file: xf-ag08-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG08
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4927 0.13865 0.13643 0.0189 1.0000 0.0075
-11.750 -0.4903 0.13519 0.13298 0.0180 1.0000 0.0075
-10.750 -0.6188 0.13314 0.13081 0.0330 1.0000 0.0069
-10.500 -0.6149 0.12938 0.12706 0.0317 1.0000 0.0064
-10.250 -0.6116 0.12527 0.12296 0.0302 1.0000 0.0060
-10.000 -0.6090 0.12084 0.11855 0.0285 1.0000 0.0056
-9.750 -0.6088 0.11559 0.11331 0.0264 1.0000 0.0052
-9.500 -0.6122 0.10889 0.10664 0.0237 1.0000 0.0048
-9.250 -0.6106 0.10432 0.10208 0.0217 1.0000 0.0047
-9.000 -0.6095 0.09975 0.09754 0.0196 1.0000 0.0047
-8.750 -0.6090 0.09509 0.09290 0.0172 1.0000 0.0047
-8.500 -0.6093 0.09033 0.08816 0.0146 1.0000 0.0047
-8.250 -0.6099 0.08555 0.08341 0.0115 1.0000 0.0048
-8.000 -0.6090 0.08044 0.07833 0.0070 1.0000 0.0049
-7.750 -0.6023 0.07418 0.07207 -0.0003 1.0000 0.0049
-7.500 -0.6248 0.02677 0.02335 -0.0383 1.0000 0.0048
-7.250 -0.6036 0.02290 0.01897 -0.0392 1.0000 0.0051
-7.000 -0.5797 0.02090 0.01666 -0.0394 1.0000 0.0053
-6.750 -0.5550 0.01918 0.01465 -0.0395 1.0000 0.0056
-6.500 -0.5299 0.01764 0.01283 -0.0395 1.0000 0.0059
-6.250 -0.5041 0.01656 0.01153 -0.0393 1.0000 0.0065
-6.000 -0.4780 0.01554 0.01026 -0.0391 1.0000 0.0071
-5.750 -0.4518 0.01460 0.00911 -0.0389 1.0000 0.0074
-5.500 -0.4261 0.01305 0.00732 -0.0387 1.0000 0.0081
-5.250 -0.3997 0.01238 0.00657 -0.0384 1.0000 0.0088
-5.000 -0.3731 0.01179 0.00588 -0.0382 1.0000 0.0096
-4.750 -0.3466 0.01123 0.00523 -0.0379 1.0000 0.0106
-4.500 -0.3200 0.01085 0.00475 -0.0375 1.0000 0.0115
-4.250 -0.2937 0.01021 0.00407 -0.0372 1.0000 0.0137
-4.000 -0.2672 0.00983 0.00364 -0.0369 1.0000 0.0155
-3.750 -0.2408 0.00950 0.00325 -0.0365 1.0000 0.0172
-3.500 -0.2146 0.00910 0.00284 -0.0361 1.0000 0.0212
-3.250 -0.1885 0.00887 0.00257 -0.0357 1.0000 0.0255
-3.000 -0.1598 0.00857 0.00229 -0.0358 0.9982 0.0327
-2.750 -0.1248 0.00831 0.00206 -0.0374 0.9912 0.0436
-2.500 -0.0897 0.00807 0.00186 -0.0389 0.9823 0.0568
-2.250 -0.0558 0.00786 0.00167 -0.0402 0.9700 0.0737
-2.000 -0.0225 0.00764 0.00152 -0.0413 0.9538 0.0937
-1.750 0.0084 0.00744 0.00139 -0.0418 0.9311 0.1212
-1.500 0.0362 0.00729 0.00126 -0.0415 0.9021 0.1521
-1.250 0.0619 0.00716 0.00116 -0.0408 0.8681 0.1914
-1.000 0.0873 0.00707 0.00107 -0.0400 0.8311 0.2358
-0.750 0.1131 0.00699 0.00102 -0.0394 0.7927 0.2913
-0.500 0.1392 0.00694 0.00096 -0.0390 0.7532 0.3464
-0.250 0.1655 0.00685 0.00094 -0.0386 0.7135 0.4216
0.000 0.1917 0.00668 0.00093 -0.0383 0.6744 0.5220
0.250 0.2153 0.00612 0.00095 -0.0374 0.6357 0.7407
0.500 0.2437 0.00574 0.00094 -0.0369 0.5948 1.0000
0.750 0.2708 0.00594 0.00095 -0.0367 0.5552 1.0000
1.000 0.2979 0.00614 0.00097 -0.0365 0.5177 1.0000
1.250 0.3251 0.00635 0.00101 -0.0363 0.4813 1.0000
1.500 0.3524 0.00656 0.00106 -0.0361 0.4460 1.0000
1.750 0.3797 0.00677 0.00114 -0.0360 0.4143 1.0000
2.000 0.4070 0.00698 0.00121 -0.0359 0.3842 1.0000
2.500 0.4616 0.00740 0.00141 -0.0356 0.3291 1.0000
2.750 0.4889 0.00762 0.00154 -0.0355 0.3032 1.0000
3.000 0.5162 0.00784 0.00167 -0.0354 0.2781 1.0000
3.250 0.5434 0.00807 0.00181 -0.0353 0.2547 1.0000
3.500 0.5706 0.00833 0.00197 -0.0351 0.2307 1.0000
3.750 0.5977 0.00858 0.00217 -0.0350 0.2074 1.0000
4.000 0.6248 0.00884 0.00236 -0.0349 0.1859 1.0000
4.250 0.6517 0.00915 0.00258 -0.0347 0.1624 1.0000
4.500 0.6785 0.00945 0.00282 -0.0346 0.1397 1.0000
4.750 0.7052 0.00980 0.00310 -0.0344 0.1167 1.0000
5.000 0.7316 0.01020 0.00340 -0.0343 0.0939 1.0000
5.250 0.7579 0.01062 0.00374 -0.0341 0.0722 1.0000
5.500 0.7842 0.01104 0.00410 -0.0339 0.0542 1.0000
5.750 0.8103 0.01150 0.00450 -0.0337 0.0388 1.0000
6.000 0.8363 0.01196 0.00495 -0.0334 0.0282 1.0000
6.250 0.8622 0.01245 0.00543 -0.0332 0.0199 1.0000
6.500 0.8880 0.01296 0.00596 -0.0329 0.0147 1.0000
6.750 0.9135 0.01353 0.00656 -0.0325 0.0117 1.0000
7.000 0.9390 0.01413 0.00725 -0.0322 0.0101 1.0000
7.250 0.9642 0.01473 0.00797 -0.0318 0.0090 1.0000
7.500 0.9891 0.01538 0.00870 -0.0314 0.0080 1.0000
7.750 1.0126 0.01636 0.00978 -0.0309 0.0069 1.0000
8.000 1.0369 0.01705 0.01058 -0.0304 0.0064 1.0000
8.250 1.0606 0.01786 0.01153 -0.0299 0.0060 1.0000
8.500 1.0837 0.01878 0.01258 -0.0293 0.0056 1.0000
8.750 1.1063 0.01975 0.01368 -0.0287 0.0053 1.0000
9.000 1.1285 0.02075 0.01485 -0.0281 0.0050 1.0000
9.250 1.1500 0.02183 0.01606 -0.0275 0.0047 1.0000
9.500 1.1699 0.02316 0.01754 -0.0267 0.0044 1.0000
9.750 1.1853 0.02531 0.01994 -0.0256 0.0042 1.0000
10.000 1.2005 0.02741 0.02231 -0.0245 0.0040 1.0000
10.250 1.2159 0.02930 0.02445 -0.0234 0.0039 1.0000
10.500 1.2284 0.03153 0.02697 -0.0222 0.0038 1.0000
10.750 1.2372 0.03413 0.02988 -0.0209 0.0038 1.0000
11.000 1.2413 0.03711 0.03318 -0.0195 0.0037 1.0000
11.250 1.2397 0.04043 0.03682 -0.0180 0.0037 1.0000
11.500 1.2298 0.04378 0.04043 -0.0163 0.0036 1.0000
11.750 1.2154 0.04796 0.04485 -0.0165 0.0036 1.0000
12.000 1.2001 0.05384 0.05096 -0.0204 0.0036 1.0000
12.250 1.1824 0.06244 0.05978 -0.0281 0.0036 1.0000
12.500 1.1623 0.07278 0.07031 -0.0366 0.0037 1.0000
12.750 1.1399 0.08331 0.08097 -0.0438 0.0037 1.0000
13.000 1.1152 0.09386 0.09161 -0.0499 0.0038 1.0000
13.250 1.0888 0.10461 0.10242 -0.0555 0.0038 1.0000
13.500 1.0610 0.11580 0.11367 -0.0610 0.0039 1.0000
13.750 1.0311 0.12796 0.12587 -0.0667 0.0040 1.0000
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