AG36 (ag36-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG36 (ag36-il) Reynolds number: 100,000 Max Cl/Cd: 50.19 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag36-il-100000.txt Download as CSV file: xf-ag36-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG36
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5007 0.10600 0.10110 -0.0011 1.0000 0.0872
-10.000 -0.5047 0.10288 0.09805 -0.0055 1.0000 0.0906
-9.750 -0.5198 0.10010 0.09539 -0.0146 1.0000 0.0919
-9.500 -0.5089 0.09474 0.09005 -0.0120 1.0000 0.0937
-9.250 -0.4927 0.09130 0.08658 -0.0089 1.0000 0.0973
-9.000 -0.4903 0.08790 0.08323 -0.0109 1.0000 0.1011
-8.750 -0.5001 0.08293 0.07817 -0.0303 1.0000 0.1062
-8.500 -0.4861 0.07843 0.07382 -0.0232 1.0000 0.1084
-8.250 -0.4741 0.07547 0.07089 -0.0212 1.0000 0.1127
-8.000 -0.4043 0.06001 0.05579 -0.0237 1.0000 0.1266
-7.750 -0.4186 0.05421 0.04978 -0.0340 1.0000 0.1350
-7.500 -0.4001 0.05159 0.04737 -0.0270 1.0000 0.1406
-7.250 -0.4330 0.05991 0.05519 -0.0310 1.0000 0.1434
-7.000 -0.4209 0.05645 0.05169 -0.0319 1.0000 0.1553
-6.750 -0.3837 0.04033 0.03604 -0.0284 1.0000 0.1699
-6.500 -0.3937 0.05005 0.04513 -0.0330 1.0000 0.1827
-6.250 -0.3789 0.04721 0.04224 -0.0327 1.0000 0.1980
-6.000 -0.3344 0.03247 0.02550 -0.0404 1.0000 0.0818
-5.750 -0.3106 0.02894 0.02139 -0.0395 1.0000 0.0738
-5.500 -0.2873 0.02621 0.01820 -0.0385 1.0000 0.0724
-5.250 -0.2635 0.02432 0.01588 -0.0375 1.0000 0.0750
-5.000 -0.2389 0.02244 0.01362 -0.0365 1.0000 0.0759
-4.750 -0.2139 0.02095 0.01178 -0.0354 1.0000 0.0778
-4.500 -0.1899 0.01935 0.01019 -0.0348 1.0000 0.0842
-4.250 -0.1651 0.01844 0.00909 -0.0339 1.0000 0.0920
-4.000 -0.1405 0.01719 0.00798 -0.0333 1.0000 0.1032
-3.750 -0.1158 0.01617 0.00712 -0.0328 1.0000 0.1247
-3.500 -0.0897 0.01487 0.00630 -0.0326 1.0000 0.1946
-3.250 -0.0708 0.01196 0.00613 -0.0297 1.0000 0.8017
-3.000 -0.0367 0.01184 0.00588 -0.0306 1.0000 1.0000
-2.750 -0.0150 0.01203 0.00582 -0.0300 1.0000 1.0000
-2.500 0.0068 0.01227 0.00583 -0.0296 1.0000 1.0000
-2.250 0.0282 0.01256 0.00596 -0.0292 1.0000 1.0000
-2.000 0.0691 0.01288 0.00609 -0.0327 0.9931 1.0000
-1.750 0.1263 0.01308 0.00610 -0.0390 0.9779 1.0000
-1.500 0.1831 0.01317 0.00606 -0.0450 0.9617 1.0000
-1.250 0.2399 0.01314 0.00594 -0.0508 0.9456 1.0000
-1.000 0.2913 0.01302 0.00576 -0.0552 0.9283 1.0000
-0.750 0.3325 0.01291 0.00560 -0.0573 0.9062 1.0000
-0.500 0.3698 0.01277 0.00541 -0.0584 0.8846 1.0000
-0.250 0.4000 0.01272 0.00530 -0.0581 0.8604 1.0000
0.000 0.4281 0.01273 0.00522 -0.0573 0.8374 1.0000
0.250 0.4539 0.01281 0.00522 -0.0561 0.8138 1.0000
0.500 0.4788 0.01297 0.00531 -0.0549 0.7903 1.0000
0.750 0.5038 0.01313 0.00537 -0.0538 0.7687 1.0000
1.000 0.5286 0.01333 0.00552 -0.0527 0.7458 1.0000
1.250 0.5537 0.01350 0.00561 -0.0517 0.7248 1.0000
1.500 0.5786 0.01370 0.00580 -0.0508 0.7019 1.0000
1.750 0.6038 0.01387 0.00589 -0.0498 0.6806 1.0000
2.000 0.6289 0.01406 0.00605 -0.0489 0.6571 1.0000
2.250 0.6542 0.01428 0.00618 -0.0480 0.6353 1.0000
2.500 0.6793 0.01460 0.00644 -0.0471 0.6123 1.0000
2.750 0.7043 0.01499 0.00678 -0.0463 0.5886 1.0000
3.000 0.7295 0.01543 0.00712 -0.0455 0.5656 1.0000
3.250 0.7542 0.01583 0.00754 -0.0448 0.5401 1.0000
3.500 0.7788 0.01621 0.00796 -0.0441 0.5147 1.0000
3.750 0.8033 0.01656 0.00829 -0.0433 0.4886 1.0000
4.000 0.8276 0.01684 0.00860 -0.0424 0.4606 1.0000
4.250 0.8514 0.01710 0.00890 -0.0416 0.4303 1.0000
4.500 0.8748 0.01743 0.00921 -0.0407 0.3975 1.0000
4.750 0.8976 0.01790 0.00957 -0.0397 0.3638 1.0000
5.000 0.9198 0.01850 0.01013 -0.0388 0.3268 1.0000
5.250 0.9413 0.01927 0.01072 -0.0379 0.2921 1.0000
5.500 0.9625 0.02007 0.01153 -0.0370 0.2558 1.0000
5.750 0.9825 0.02098 0.01229 -0.0361 0.2218 1.0000
6.000 1.0020 0.02197 0.01325 -0.0351 0.1856 1.0000
6.250 1.0195 0.02327 0.01436 -0.0340 0.1512 1.0000
6.500 1.0362 0.02484 0.01587 -0.0326 0.1167 1.0000
6.750 1.0523 0.02674 0.01771 -0.0311 0.0918 1.0000
7.000 1.0692 0.02859 0.01947 -0.0298 0.0758 1.0000
7.250 1.0880 0.03077 0.02175 -0.0285 0.0658 1.0000
7.500 1.1064 0.03310 0.02414 -0.0275 0.0584 1.0000
7.750 1.1260 0.03546 0.02672 -0.0263 0.0538 1.0000
8.000 1.1451 0.03926 0.03051 -0.0258 0.0501 1.0000
8.250 1.1579 0.04160 0.03344 -0.0239 0.0477 1.0000
8.500 1.1686 0.04455 0.03685 -0.0222 0.0454 1.0000
8.750 1.1752 0.04819 0.04093 -0.0203 0.0445 1.0000
9.000 1.1759 0.05218 0.04539 -0.0182 0.0442 1.0000
9.250 1.1695 0.05645 0.05011 -0.0160 0.0443 1.0000
9.500 1.1563 0.06082 0.05488 -0.0138 0.0447 1.0000
9.750 1.1362 0.06494 0.05929 -0.0116 0.0451 1.0000
10.000 1.1134 0.06957 0.06419 -0.0110 0.0455 1.0000
10.250 1.0892 0.07502 0.06986 -0.0124 0.0460 1.0000
10.500 1.0636 0.08154 0.07657 -0.0157 0.0466 1.0000
10.750 1.0372 0.08939 0.08458 -0.0209 0.0473 1.0000
11.000 1.0108 0.09844 0.09372 -0.0270 0.0481 1.0000
11.250 0.9876 0.10790 0.10320 -0.0329 0.0489 1.0000
11.500 0.9722 0.11626 0.11156 -0.0370 0.0497 1.0000
11.750 0.7246 0.13316 0.12853 -0.0344 0.0697 1.0000
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Polar data table (+)
Polar graphs
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