AG04 (ag04-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG04 (ag04-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.04 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag04-il-1000000-n5.txt Download as CSV file: xf-ag04-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG04
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6097 0.11516 0.11356 0.0278 1.0000 0.0035
-9.500 -0.6103 0.10983 0.10825 0.0257 1.0000 0.0032
-8.000 -0.6864 0.02337 0.02038 -0.0368 1.0000 0.0024
-7.750 -0.6651 0.02016 0.01673 -0.0372 1.0000 0.0025
-7.500 -0.6412 0.01828 0.01455 -0.0372 1.0000 0.0026
-7.250 -0.6161 0.01700 0.01305 -0.0371 1.0000 0.0026
-7.000 -0.5928 0.01440 0.01001 -0.0370 1.0000 0.0030
-6.750 -0.5666 0.01366 0.00917 -0.0369 1.0000 0.0032
-6.500 -0.5402 0.01301 0.00841 -0.0368 1.0000 0.0033
-6.250 -0.5136 0.01239 0.00768 -0.0366 1.0000 0.0035
-6.000 -0.4870 0.01179 0.00698 -0.0364 1.0000 0.0037
-5.750 -0.4603 0.01116 0.00624 -0.0362 1.0000 0.0039
-5.500 -0.4335 0.01058 0.00557 -0.0360 1.0000 0.0041
-5.250 -0.4067 0.01007 0.00498 -0.0358 1.0000 0.0042
-5.000 -0.3798 0.00962 0.00446 -0.0355 1.0000 0.0044
-4.750 -0.3529 0.00931 0.00411 -0.0353 1.0000 0.0047
-4.500 -0.3247 0.00882 0.00353 -0.0353 0.9981 0.0050
-4.250 -0.2916 0.00834 0.00297 -0.0365 0.9882 0.0057
-4.000 -0.2578 0.00800 0.00261 -0.0377 0.9743 0.0066
-3.750 -0.2253 0.00775 0.00230 -0.0386 0.9558 0.0076
-3.500 -0.1974 0.00753 0.00201 -0.0383 0.9312 0.0103
-3.250 -0.1715 0.00739 0.00179 -0.0376 0.9035 0.0141
-3.000 -0.1457 0.00727 0.00160 -0.0370 0.8736 0.0215
-2.750 -0.1194 0.00713 0.00143 -0.0365 0.8427 0.0353
-2.500 -0.0927 0.00704 0.00128 -0.0361 0.8106 0.0515
-2.250 -0.0657 0.00696 0.00114 -0.0358 0.7778 0.0722
-2.000 -0.0385 0.00691 0.00103 -0.0356 0.7459 0.0914
-1.750 -0.0110 0.00685 0.00093 -0.0355 0.7154 0.1155
-1.500 0.0165 0.00679 0.00085 -0.0354 0.6868 0.1438
-1.250 0.0442 0.00674 0.00078 -0.0353 0.6574 0.1731
-1.000 0.0719 0.00670 0.00072 -0.0352 0.6290 0.2038
-0.750 0.0996 0.00665 0.00068 -0.0352 0.6006 0.2425
-0.500 0.1273 0.00661 0.00066 -0.0351 0.5725 0.2808
-0.250 0.1550 0.00656 0.00064 -0.0351 0.5442 0.3270
0.000 0.1827 0.00652 0.00064 -0.0351 0.5159 0.3757
0.250 0.2103 0.00647 0.00065 -0.0351 0.4871 0.4332
0.750 0.2653 0.00635 0.00071 -0.0351 0.4316 0.5676
1.000 0.2922 0.00619 0.00075 -0.0350 0.4045 0.6689
1.250 0.3141 0.00567 0.00082 -0.0335 0.3809 0.8800
1.500 0.3462 0.00564 0.00085 -0.0342 0.3550 1.0000
1.750 0.3739 0.00581 0.00091 -0.0342 0.3304 1.0000
2.000 0.4016 0.00597 0.00098 -0.0341 0.3082 1.0000
2.250 0.4293 0.00614 0.00105 -0.0340 0.2853 1.0000
2.500 0.4569 0.00633 0.00114 -0.0340 0.2630 1.0000
2.750 0.4845 0.00651 0.00125 -0.0339 0.2425 1.0000
3.000 0.5120 0.00671 0.00136 -0.0338 0.2205 1.0000
3.250 0.5396 0.00690 0.00147 -0.0337 0.2019 1.0000
3.500 0.5670 0.00712 0.00160 -0.0337 0.1813 1.0000
3.750 0.5944 0.00733 0.00176 -0.0336 0.1646 1.0000
4.000 0.6218 0.00755 0.00192 -0.0335 0.1457 1.0000
4.250 0.6491 0.00779 0.00209 -0.0334 0.1291 1.0000
4.500 0.6762 0.00806 0.00228 -0.0333 0.1114 1.0000
4.750 0.7034 0.00831 0.00249 -0.0332 0.0969 1.0000
5.000 0.7304 0.00860 0.00272 -0.0331 0.0804 1.0000
5.250 0.7572 0.00891 0.00297 -0.0330 0.0654 1.0000
5.500 0.7841 0.00922 0.00323 -0.0328 0.0535 1.0000
5.750 0.8108 0.00954 0.00351 -0.0327 0.0432 1.0000
6.000 0.8375 0.00987 0.00383 -0.0325 0.0344 1.0000
6.250 0.8640 0.01022 0.00415 -0.0324 0.0266 1.0000
6.500 0.8903 0.01060 0.00450 -0.0322 0.0203 1.0000
6.750 0.9168 0.01094 0.00485 -0.0320 0.0160 1.0000
7.000 0.9429 0.01136 0.00526 -0.0318 0.0118 1.0000
7.250 0.9691 0.01171 0.00564 -0.0316 0.0101 1.0000
7.500 0.9949 0.01216 0.00612 -0.0313 0.0079 1.0000
7.750 1.0208 0.01257 0.00658 -0.0311 0.0067 1.0000
8.000 1.0465 0.01301 0.00706 -0.0308 0.0056 1.0000
8.250 1.0714 0.01360 0.00769 -0.0305 0.0044 1.0000
8.500 1.0968 0.01406 0.00821 -0.0302 0.0039 1.0000
8.750 1.1218 0.01456 0.00877 -0.0299 0.0034 1.0000
9.000 1.1464 0.01513 0.00940 -0.0295 0.0030 1.0000
9.250 1.1703 0.01584 0.01020 -0.0291 0.0026 1.0000
9.500 1.1933 0.01671 0.01119 -0.0286 0.0023 1.0000
9.750 1.2170 0.01738 0.01196 -0.0281 0.0023 1.0000
10.000 1.2401 0.01811 0.01279 -0.0276 0.0022 1.0000
10.250 1.2627 0.01890 0.01369 -0.0271 0.0021 1.0000
10.500 1.2847 0.01976 0.01467 -0.0266 0.0020 1.0000
10.750 1.3061 0.02067 0.01569 -0.0260 0.0019 1.0000
11.000 1.3268 0.02163 0.01678 -0.0253 0.0018 1.0000
11.250 1.3469 0.02265 0.01794 -0.0246 0.0017 1.0000
11.500 1.3662 0.02370 0.01913 -0.0239 0.0016 1.0000
11.750 1.3845 0.02484 0.02039 -0.0231 0.0015 1.0000
12.000 1.4014 0.02609 0.02177 -0.0222 0.0014 1.0000
12.250 1.4163 0.02752 0.02335 -0.0212 0.0013 1.0000
12.500 1.4278 0.02926 0.02527 -0.0200 0.0013 1.0000
12.750 1.4334 0.03153 0.02775 -0.0185 0.0012 1.0000
13.000 1.4274 0.03458 0.03107 -0.0163 0.0011 1.0000
13.250 1.4130 0.03785 0.03457 -0.0141 0.0011 1.0000
13.500 1.3987 0.04205 0.03897 -0.0147 0.0011 1.0000
13.750 1.3865 0.04733 0.04443 -0.0178 0.0011 1.0000
14.000 1.3686 0.05507 0.05239 -0.0238 0.0011 1.0000
14.500 1.3283 0.07332 0.07096 -0.0366 0.0011 1.0000
14.750 1.3038 0.08291 0.08066 -0.0419 0.0011 1.0000
15.000 1.2794 0.09214 0.08998 -0.0465 0.0012 1.0000
15.250 1.2500 0.10225 0.10019 -0.0514 0.0012 1.0000
15.500 1.2169 0.11317 0.11120 -0.0566 0.0013 1.0000
15.750 1.1814 0.12491 0.12303 -0.0623 0.0014 1.0000
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Polar data table (+)
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