AG18 (ag18-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG18 (ag18-il) Reynolds number: 100,000 Max Cl/Cd: 50.76 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag18-il-100000.txt Download as CSV file: xf-ag18-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG18
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5476 0.11717 0.11228 0.0159 1.0000 0.0624
-8.750 -0.5498 0.11506 0.11023 0.0108 1.0000 0.0636
-8.500 -0.5515 0.11272 0.10797 0.0054 1.0000 0.0640
-8.250 -0.5329 0.10576 0.10098 0.0118 1.0000 0.0678
-8.000 -0.5261 0.10243 0.09768 0.0109 1.0000 0.0718
-7.750 -0.5239 0.09938 0.09469 0.0075 1.0000 0.0752
-7.500 -0.5229 0.09662 0.09201 -0.0025 1.0000 0.0769
-7.250 -0.5157 0.09139 0.08684 -0.0030 1.0000 0.0787
-7.000 -0.5045 0.08783 0.08329 0.0008 1.0000 0.0825
-6.750 -0.4936 0.08398 0.07946 -0.0035 1.0000 0.0871
-6.500 -0.4753 0.07809 0.07354 -0.0202 1.0000 0.0915
-6.250 -0.4677 0.07495 0.07047 -0.0133 1.0000 0.0947
-6.000 -0.4391 0.06917 0.06445 -0.0307 1.0000 0.1047
-5.750 -0.4318 0.06565 0.06111 -0.0242 1.0000 0.1072
-5.500 -0.4054 0.06053 0.05578 -0.0337 1.0000 0.1188
-5.250 -0.3931 0.05749 0.05282 -0.0303 1.0000 0.1230
-5.000 -0.3694 0.05305 0.04825 -0.0350 1.0000 0.1349
-4.750 -0.3461 0.04918 0.04427 -0.0380 1.0000 0.1483
-4.500 -0.3230 0.04567 0.04067 -0.0398 1.0000 0.1625
-4.250 -0.2635 0.03188 0.02532 -0.0506 1.0000 0.0681
-4.000 -0.2320 0.02724 0.01999 -0.0514 1.0000 0.0573
-3.750 -0.2030 0.02445 0.01667 -0.0516 1.0000 0.0591
-3.500 -0.1739 0.02201 0.01369 -0.0514 1.0000 0.0611
-3.250 -0.1451 0.01977 0.01100 -0.0509 1.0000 0.0623
-3.000 -0.1174 0.01767 0.00871 -0.0503 1.0000 0.0670
-2.750 -0.0909 0.01637 0.00743 -0.0499 1.0000 0.0831
-2.500 -0.0640 0.01491 0.00604 -0.0493 1.0000 0.1105
-2.250 -0.0370 0.01322 0.00491 -0.0492 1.0000 0.2083
-2.000 -0.0124 0.01161 0.00453 -0.0488 1.0000 0.4781
-1.750 0.0052 0.01038 0.00430 -0.0457 1.0000 0.7432
-1.500 0.0316 0.00988 0.00386 -0.0446 1.0000 1.0000
-1.250 0.0583 0.00992 0.00358 -0.0445 1.0000 1.0000
-1.000 0.0846 0.00998 0.00341 -0.0443 1.0000 1.0000
-0.750 0.1106 0.01007 0.00331 -0.0442 1.0000 1.0000
-0.500 0.1362 0.01018 0.00327 -0.0440 1.0000 1.0000
-0.250 0.1617 0.01031 0.00329 -0.0439 1.0000 1.0000
0.000 0.1872 0.01048 0.00335 -0.0439 1.0000 1.0000
0.250 0.2123 0.01070 0.00349 -0.0439 1.0000 1.0000
0.500 0.2371 0.01096 0.00371 -0.0440 1.0000 1.0000
0.750 0.2615 0.01129 0.00401 -0.0443 1.0000 1.0000
1.000 0.2999 0.01162 0.00434 -0.0473 0.9923 1.0000
1.250 0.3596 0.01177 0.00452 -0.0539 0.9709 1.0000
1.500 0.4146 0.01176 0.00458 -0.0590 0.9475 1.0000
1.750 0.4602 0.01169 0.00460 -0.0618 0.9201 1.0000
2.000 0.4965 0.01161 0.00457 -0.0622 0.8884 1.0000
2.250 0.5243 0.01161 0.00456 -0.0609 0.8516 1.0000
2.500 0.5488 0.01167 0.00458 -0.0588 0.8119 1.0000
2.750 0.5719 0.01180 0.00463 -0.0566 0.7687 1.0000
3.000 0.5947 0.01201 0.00475 -0.0544 0.7228 1.0000
3.250 0.6178 0.01229 0.00489 -0.0526 0.6716 1.0000
3.500 0.6410 0.01265 0.00506 -0.0509 0.6176 1.0000
3.750 0.6645 0.01309 0.00529 -0.0494 0.5618 1.0000
4.000 0.6881 0.01363 0.00559 -0.0481 0.5061 1.0000
4.250 0.7119 0.01425 0.00604 -0.0470 0.4522 1.0000
4.500 0.7359 0.01493 0.00651 -0.0461 0.4018 1.0000
4.750 0.7598 0.01568 0.00706 -0.0453 0.3549 1.0000
5.000 0.7837 0.01650 0.00768 -0.0446 0.3115 1.0000
5.250 0.8077 0.01738 0.00840 -0.0439 0.2709 1.0000
5.500 0.8317 0.01829 0.00928 -0.0433 0.2324 1.0000
5.750 0.8556 0.01935 0.01025 -0.0427 0.1992 1.0000
6.000 0.8794 0.02042 0.01128 -0.0420 0.1686 1.0000
6.250 0.9031 0.02175 0.01258 -0.0413 0.1437 1.0000
6.500 0.9262 0.02313 0.01388 -0.0406 0.1209 1.0000
6.750 0.9498 0.02474 0.01563 -0.0398 0.1018 1.0000
7.000 0.9724 0.02644 0.01730 -0.0390 0.0852 1.0000
7.250 0.9952 0.02862 0.01970 -0.0381 0.0724 1.0000
7.500 1.0172 0.03094 0.02239 -0.0371 0.0618 1.0000
7.750 1.0373 0.03451 0.02635 -0.0359 0.0556 1.0000
8.000 1.0566 0.03657 0.02859 -0.0351 0.0480 1.0000
8.250 1.0700 0.04183 0.03439 -0.0339 0.0459 1.0000
8.500 1.0800 0.04661 0.03993 -0.0324 0.0451 1.0000
8.750 1.0844 0.05201 0.04597 -0.0313 0.0448 1.0000
9.000 1.0830 0.05755 0.05206 -0.0305 0.0445 1.0000
9.250 1.0762 0.06320 0.05814 -0.0302 0.0445 1.0000
9.500 1.0648 0.06882 0.06407 -0.0304 0.0447 1.0000
9.750 1.0498 0.07420 0.06964 -0.0311 0.0452 1.0000
10.000 1.0335 0.07958 0.07513 -0.0324 0.0457 1.0000
10.250 1.0198 0.08574 0.08134 -0.0349 0.0463 1.0000
10.500 0.9372 0.11985 0.11547 -0.0658 0.0867 1.0000
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Polar data table (+)
Polar graphs
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