AG17 (ag17-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG17 (ag17-il) Reynolds number: 500,000 Max Cl/Cd: 76.67 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag17-il-500000-n5.txt Download as CSV file: xf-ag17-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG17
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5655 0.09896 0.09675 0.0145 1.0000 0.0054
-8.500 -0.5633 0.09479 0.09260 0.0123 1.0000 0.0053
-8.250 -0.5610 0.09055 0.08839 0.0100 1.0000 0.0051
-8.000 -0.5589 0.08622 0.08408 0.0073 1.0000 0.0050
-7.750 -0.5568 0.08168 0.07957 0.0040 1.0000 0.0050
-7.500 -0.5504 0.07632 0.07423 -0.0016 1.0000 0.0049
-7.250 -0.5397 0.06985 0.06777 -0.0095 1.0000 0.0048
-7.000 -0.5242 0.06181 0.05970 -0.0199 1.0000 0.0046
-6.750 -0.5029 0.05047 0.04822 -0.0334 1.0000 0.0045
-6.500 -0.4832 0.02950 0.02637 -0.0474 1.0000 0.0042
-6.250 -0.4603 0.02095 0.01680 -0.0501 1.0000 0.0044
-6.000 -0.4346 0.01795 0.01329 -0.0505 1.0000 0.0048
-5.750 -0.4083 0.01613 0.01111 -0.0505 1.0000 0.0052
-5.500 -0.3819 0.01489 0.00963 -0.0504 1.0000 0.0055
-5.250 -0.3553 0.01398 0.00850 -0.0502 1.0000 0.0056
-5.000 -0.3292 0.01247 0.00679 -0.0501 1.0000 0.0063
-4.750 -0.3029 0.01204 0.00633 -0.0499 1.0000 0.0071
-4.500 -0.2765 0.01148 0.00569 -0.0496 1.0000 0.0077
-4.250 -0.2500 0.01073 0.00484 -0.0493 1.0000 0.0081
-4.000 -0.2235 0.01012 0.00412 -0.0490 1.0000 0.0087
-3.750 -0.1949 0.00964 0.00353 -0.0491 0.9986 0.0095
-3.500 -0.1599 0.00904 0.00285 -0.0506 0.9923 0.0120
-3.250 -0.1252 0.00872 0.00248 -0.0520 0.9835 0.0158
-3.000 -0.0910 0.00834 0.00215 -0.0533 0.9722 0.0298
-2.750 -0.0573 0.00801 0.00190 -0.0545 0.9581 0.0537
-2.500 -0.0249 0.00771 0.00168 -0.0554 0.9396 0.0882
-2.250 0.0041 0.00743 0.00150 -0.0556 0.9159 0.1313
-2.000 0.0309 0.00721 0.00136 -0.0551 0.8893 0.1784
-1.750 0.0570 0.00705 0.00125 -0.0546 0.8611 0.2260
-1.500 0.0832 0.00694 0.00115 -0.0540 0.8319 0.2711
-1.250 0.1097 0.00687 0.00107 -0.0536 0.8024 0.3137
-1.000 0.1364 0.00682 0.00102 -0.0532 0.7727 0.3569
-0.750 0.1633 0.00676 0.00098 -0.0529 0.7434 0.4061
-0.500 0.1903 0.00673 0.00095 -0.0526 0.7140 0.4522
-0.250 0.2174 0.00670 0.00094 -0.0524 0.6849 0.5011
0.250 0.2712 0.00659 0.00096 -0.0519 0.6258 0.6223
0.500 0.2973 0.00645 0.00100 -0.0514 0.5952 0.7114
0.750 0.3169 0.00602 0.00101 -0.0491 0.5671 0.8955
1.000 0.3487 0.00610 0.00101 -0.0498 0.5342 1.0000
1.250 0.3762 0.00629 0.00105 -0.0497 0.5026 1.0000
1.500 0.4038 0.00649 0.00110 -0.0496 0.4712 1.0000
1.750 0.4313 0.00670 0.00118 -0.0495 0.4403 1.0000
2.000 0.4587 0.00691 0.00126 -0.0494 0.4101 1.0000
2.250 0.4862 0.00714 0.00135 -0.0493 0.3801 1.0000
2.500 0.5136 0.00737 0.00146 -0.0492 0.3511 1.0000
2.750 0.5409 0.00761 0.00161 -0.0491 0.3232 1.0000
3.000 0.5682 0.00786 0.00175 -0.0490 0.2959 1.0000
3.500 0.6227 0.00838 0.00207 -0.0488 0.2432 1.0000
3.750 0.6499 0.00865 0.00226 -0.0487 0.2201 1.0000
4.000 0.6769 0.00894 0.00248 -0.0486 0.1961 1.0000
4.500 0.7308 0.00956 0.00295 -0.0483 0.1516 1.0000
4.750 0.7576 0.00990 0.00322 -0.0482 0.1318 1.0000
5.000 0.7843 0.01023 0.00353 -0.0480 0.1133 1.0000
5.250 0.8107 0.01063 0.00385 -0.0478 0.0938 1.0000
5.500 0.8372 0.01102 0.00419 -0.0477 0.0771 1.0000
5.750 0.8635 0.01143 0.00456 -0.0475 0.0623 1.0000
6.000 0.8897 0.01185 0.00496 -0.0473 0.0504 1.0000
6.250 0.9156 0.01231 0.00539 -0.0470 0.0388 1.0000
6.500 0.9414 0.01279 0.00589 -0.0468 0.0294 1.0000
6.750 0.9670 0.01331 0.00641 -0.0465 0.0216 1.0000
7.000 0.9922 0.01390 0.00698 -0.0462 0.0149 1.0000
7.250 1.0177 0.01441 0.00754 -0.0459 0.0115 1.0000
7.500 1.0423 0.01514 0.00831 -0.0454 0.0084 1.0000
7.750 1.0672 0.01574 0.00902 -0.0450 0.0071 1.0000
8.000 1.0915 0.01648 0.00984 -0.0446 0.0059 1.0000
8.250 1.1137 0.01770 0.01122 -0.0439 0.0049 1.0000
8.500 1.1372 0.01852 0.01221 -0.0433 0.0046 1.0000
8.750 1.1603 0.01935 0.01316 -0.0428 0.0041 1.0000
9.000 1.1833 0.02016 0.01408 -0.0423 0.0037 1.0000
9.250 1.2057 0.02103 0.01506 -0.0417 0.0033 1.0000
9.500 1.2268 0.02210 0.01627 -0.0411 0.0031 1.0000
9.750 1.2465 0.02340 0.01773 -0.0403 0.0029 1.0000
10.000 1.2630 0.02517 0.01971 -0.0392 0.0027 1.0000
10.250 1.2764 0.02736 0.02216 -0.0379 0.0025 1.0000
10.500 1.2923 0.02896 0.02397 -0.0369 0.0025 1.0000
10.750 1.3059 0.03078 0.02605 -0.0357 0.0024 1.0000
11.000 1.3166 0.03286 0.02839 -0.0344 0.0023 1.0000
11.250 1.3237 0.03518 0.03096 -0.0330 0.0022 1.0000
11.500 1.3259 0.03782 0.03387 -0.0314 0.0022 1.0000
11.750 1.3202 0.04061 0.03690 -0.0293 0.0021 1.0000
12.000 1.3098 0.04403 0.04054 -0.0284 0.0021 1.0000
12.250 1.2973 0.04856 0.04530 -0.0297 0.0020 1.0000
12.500 1.2832 0.05456 0.05153 -0.0335 0.0020 1.0000
12.750 1.2664 0.06236 0.05954 -0.0394 0.0021 1.0000
13.000 1.2473 0.07150 0.06887 -0.0462 0.0021 1.0000
13.250 1.2245 0.08157 0.07909 -0.0528 0.0021 1.0000
13.500 1.1997 0.09190 0.08954 -0.0588 0.0022 1.0000
13.750 1.1733 0.10241 0.10015 -0.0643 0.0022 1.0000
14.000 1.1469 0.11289 0.11071 -0.0695 0.0023 1.0000
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Polar data table (+)
Polar graphs
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