AG11 (ag11-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG11 (ag11-il) Reynolds number: 1,000,000 Max Cl/Cd: 90.99 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag11-il-1000000-n5.txt Download as CSV file: xf-ag11-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG11
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4254 0.08571 0.08422 0.0061 1.0000 0.0046
-8.000 -0.4237 0.08206 0.08059 0.0050 1.0000 0.0047
-7.750 -0.4222 0.07841 0.07695 0.0039 1.0000 0.0049
-7.500 -0.4211 0.07468 0.07323 0.0027 1.0000 0.0051
-7.250 -0.4210 0.07081 0.06937 0.0012 1.0000 0.0052
-7.000 -0.4211 0.06704 0.06562 -0.0005 1.0000 0.0054
-6.750 -0.4187 0.06274 0.06133 -0.0039 1.0000 0.0058
-6.500 -0.4111 0.05772 0.05630 -0.0088 1.0000 0.0062
-6.250 -0.3997 0.05228 0.05083 -0.0144 1.0000 0.0064
-6.000 -0.3847 0.04688 0.04538 -0.0195 1.0000 0.0065
-5.750 -0.3688 0.04197 0.04041 -0.0230 1.0000 0.0065
-5.500 -0.3517 0.03726 0.03563 -0.0259 1.0000 0.0065
-5.250 -0.3303 0.03235 0.03062 -0.0291 0.9948 0.0065
-5.000 -0.3035 0.02733 0.02548 -0.0327 0.9809 0.0065
-4.750 -0.2760 0.02272 0.02071 -0.0356 0.9633 0.0066
-4.500 -0.2513 0.01874 0.01653 -0.0370 0.9431 0.0066
-4.250 -0.2479 0.03197 0.02944 -0.0375 0.9730 0.0066
-3.250 -0.1391 0.01542 0.01129 -0.0373 0.8784 0.0040
-3.000 -0.1122 0.01225 0.00754 -0.0363 0.8514 0.0039
-2.750 -0.0853 0.01049 0.00534 -0.0356 0.8219 0.0039
-2.500 -0.0584 0.00955 0.00411 -0.0350 0.7906 0.0039
-2.250 -0.0313 0.00899 0.00331 -0.0346 0.7592 0.0040
-2.000 -0.0038 0.00865 0.00278 -0.0344 0.7294 0.0042
-1.750 0.0237 0.00818 0.00214 -0.0342 0.6998 0.0048
-1.500 0.0515 0.00806 0.00189 -0.0341 0.6706 0.0054
-1.250 0.0794 0.00795 0.00165 -0.0340 0.6401 0.0060
-1.000 0.1074 0.00788 0.00145 -0.0339 0.6111 0.0064
-0.750 0.1354 0.00779 0.00125 -0.0339 0.5816 0.0076
-0.500 0.1634 0.00777 0.00112 -0.0338 0.5526 0.0089
-0.250 0.1915 0.00774 0.00098 -0.0338 0.5238 0.0122
0.000 0.2195 0.00773 0.00090 -0.0338 0.4920 0.0273
0.250 0.2474 0.00760 0.00088 -0.0339 0.4615 0.1035
0.500 0.2750 0.00697 0.00088 -0.0343 0.4341 0.3846
0.750 0.2984 0.00577 0.00095 -0.0338 0.4060 0.8382
1.000 0.3254 0.00557 0.00093 -0.0332 0.3791 1.0000
1.250 0.3533 0.00573 0.00096 -0.0332 0.3543 1.0000
1.500 0.3811 0.00591 0.00099 -0.0332 0.3277 1.0000
1.750 0.4089 0.00609 0.00104 -0.0332 0.3016 1.0000
2.000 0.4367 0.00627 0.00110 -0.0332 0.2778 1.0000
2.250 0.4645 0.00646 0.00117 -0.0331 0.2535 1.0000
2.500 0.4922 0.00666 0.00126 -0.0331 0.2304 1.0000
2.750 0.5199 0.00685 0.00135 -0.0331 0.2103 1.0000
3.000 0.5475 0.00706 0.00145 -0.0331 0.1897 1.0000
3.250 0.5751 0.00726 0.00156 -0.0331 0.1724 1.0000
3.500 0.6028 0.00744 0.00168 -0.0331 0.1582 1.0000
3.750 0.6303 0.00764 0.00182 -0.0330 0.1447 1.0000
4.000 0.6578 0.00786 0.00196 -0.0330 0.1290 1.0000
4.250 0.6852 0.00809 0.00212 -0.0330 0.1148 1.0000
4.500 0.7126 0.00831 0.00228 -0.0329 0.1041 1.0000
4.750 0.7399 0.00853 0.00248 -0.0329 0.0941 1.0000
5.000 0.7671 0.00878 0.00267 -0.0328 0.0839 1.0000
5.250 0.7943 0.00903 0.00288 -0.0328 0.0744 1.0000
5.500 0.8214 0.00925 0.00308 -0.0327 0.0678 1.0000
5.750 0.8484 0.00952 0.00333 -0.0326 0.0613 1.0000
6.000 0.8755 0.00974 0.00356 -0.0326 0.0571 1.0000
6.250 0.9024 0.01002 0.00381 -0.0325 0.0519 1.0000
6.500 0.9292 0.01029 0.00410 -0.0324 0.0476 1.0000
6.750 0.9560 0.01052 0.00436 -0.0323 0.0454 1.0000
7.000 0.9827 0.01080 0.00465 -0.0322 0.0425 1.0000
7.250 1.0091 0.01113 0.00498 -0.0320 0.0391 1.0000
7.500 1.0355 0.01142 0.00531 -0.0319 0.0368 1.0000
7.750 1.0620 0.01169 0.00563 -0.0318 0.0351 1.0000
8.000 1.0881 0.01202 0.00598 -0.0316 0.0329 1.0000
8.250 1.1139 0.01241 0.00637 -0.0314 0.0300 1.0000
8.500 1.1396 0.01279 0.00679 -0.0312 0.0279 1.0000
8.750 1.1655 0.01311 0.00719 -0.0311 0.0268 1.0000
9.000 1.1910 0.01348 0.00759 -0.0309 0.0249 1.0000
9.250 1.2162 0.01391 0.00806 -0.0306 0.0230 1.0000
9.500 1.2408 0.01442 0.00860 -0.0303 0.0205 1.0000
9.750 1.2660 0.01479 0.00902 -0.0301 0.0189 1.0000
10.000 1.2903 0.01530 0.00953 -0.0299 0.0163 1.0000
10.250 1.3142 0.01585 0.01014 -0.0295 0.0143 1.0000
10.500 1.3383 0.01635 0.01071 -0.0292 0.0131 1.0000
10.750 1.3616 0.01695 0.01134 -0.0288 0.0114 1.0000
11.000 1.3845 0.01760 0.01205 -0.0284 0.0098 1.0000
11.250 1.4071 0.01825 0.01277 -0.0279 0.0085 1.0000
11.500 1.4285 0.01906 0.01363 -0.0274 0.0070 1.0000
11.750 1.4501 0.01981 0.01446 -0.0268 0.0060 1.0000
12.000 1.4702 0.02072 0.01547 -0.0261 0.0048 1.0000
12.250 1.4899 0.02164 0.01649 -0.0254 0.0040 1.0000
12.500 1.5085 0.02266 0.01761 -0.0246 0.0033 1.0000
12.750 1.5256 0.02381 0.01887 -0.0237 0.0026 1.0000
13.000 1.5424 0.02491 0.02009 -0.0227 0.0022 1.0000
13.250 1.5570 0.02619 0.02150 -0.0216 0.0019 1.0000
13.500 1.5691 0.02767 0.02311 -0.0203 0.0016 1.0000
13.750 1.5805 0.02908 0.02467 -0.0190 0.0014 1.0000
14.000 1.5898 0.03054 0.02628 -0.0175 0.0013 1.0000
14.250 1.5939 0.03213 0.02802 -0.0154 0.0013 1.0000
14.500 1.5924 0.03398 0.03002 -0.0131 0.0012 1.0000
14.750 1.5884 0.03634 0.03253 -0.0116 0.0012 1.0000
15.000 1.5817 0.03942 0.03578 -0.0113 0.0011 1.0000
15.250 1.5730 0.04338 0.03990 -0.0124 0.0011 1.0000
15.500 1.5600 0.04872 0.04542 -0.0152 0.0010 1.0000
15.750 1.5420 0.05573 0.05263 -0.0197 0.0010 1.0000
16.000 1.5160 0.06490 0.06200 -0.0258 0.0011 1.0000
16.250 1.4765 0.07698 0.07428 -0.0332 0.0011 1.0000
16.500 1.4238 0.09144 0.08894 -0.0411 0.0012 1.0000
16.750 1.3580 0.10841 0.10607 -0.0496 0.0014 1.0000
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Polar data table (+)
Polar graphs
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