AG36 (ag36-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG36 (ag36-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.04 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag36-il-1000000-n5.txt Download as CSV file: xf-ag36-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5684 0.12498 0.12332 0.0142 1.0000 0.0050
-12.250 -0.5661 0.12069 0.11903 0.0124 1.0000 0.0050
-11.250 -0.7978 0.03210 0.02976 -0.0480 1.0000 0.0057
-11.000 -0.7948 0.02531 0.02230 -0.0487 1.0000 0.0058
-10.750 -0.7774 0.02267 0.01932 -0.0484 1.0000 0.0059
-10.500 -0.7569 0.02085 0.01723 -0.0480 1.0000 0.0060
-10.250 -0.7350 0.01940 0.01556 -0.0475 1.0000 0.0061
-10.000 -0.7123 0.01822 0.01419 -0.0469 1.0000 0.0062
-9.750 -0.6896 0.01700 0.01277 -0.0463 1.0000 0.0063
-9.500 -0.6679 0.01549 0.01103 -0.0456 1.0000 0.0065
-9.250 -0.6446 0.01463 0.01005 -0.0449 1.0000 0.0067
-9.000 -0.6153 0.01395 0.00926 -0.0454 0.9977 0.0069
-8.750 -0.5842 0.01336 0.00859 -0.0462 0.9948 0.0071
-8.500 -0.5539 0.01279 0.00794 -0.0468 0.9904 0.0074
-8.250 -0.5226 0.01228 0.00736 -0.0476 0.9853 0.0077
-8.000 -0.4920 0.01179 0.00679 -0.0481 0.9786 0.0080
-7.750 -0.4615 0.01137 0.00629 -0.0487 0.9709 0.0084
-7.500 -0.4329 0.01096 0.00580 -0.0487 0.9619 0.0087
-7.250 -0.4050 0.01058 0.00534 -0.0486 0.9507 0.0089
-7.000 -0.3789 0.01003 0.00469 -0.0481 0.9359 0.0093
-6.750 -0.3528 0.00968 0.00427 -0.0476 0.9192 0.0098
-6.500 -0.3269 0.00943 0.00392 -0.0469 0.8970 0.0103
-6.250 -0.3011 0.00924 0.00361 -0.0463 0.8686 0.0108
-6.000 -0.2745 0.00905 0.00330 -0.0458 0.8475 0.0114
-5.750 -0.2473 0.00888 0.00302 -0.0455 0.8291 0.0120
-5.500 -0.2199 0.00870 0.00274 -0.0452 0.8128 0.0127
-5.250 -0.1924 0.00851 0.00249 -0.0450 0.7981 0.0142
-5.000 -0.1646 0.00837 0.00229 -0.0449 0.7839 0.0153
-4.750 -0.1367 0.00825 0.00210 -0.0448 0.7692 0.0165
-4.500 -0.1088 0.00811 0.00189 -0.0446 0.7535 0.0186
-4.250 -0.0809 0.00800 0.00173 -0.0445 0.7342 0.0211
-4.000 -0.0530 0.00794 0.00158 -0.0444 0.7107 0.0245
-3.750 -0.0252 0.00787 0.00144 -0.0443 0.6777 0.0300
-3.500 0.0018 0.00796 0.00131 -0.0441 0.6134 0.0387
-3.250 0.0296 0.00792 0.00123 -0.0441 0.5888 0.0534
-3.000 0.0576 0.00783 0.00115 -0.0441 0.5719 0.0765
-2.750 0.0857 0.00772 0.00108 -0.0442 0.5587 0.1068
-2.500 0.1138 0.00756 0.00103 -0.0442 0.5473 0.1525
-2.250 0.1418 0.00740 0.00098 -0.0443 0.5370 0.2066
-2.000 0.1698 0.00719 0.00095 -0.0445 0.5280 0.2780
-1.750 0.1979 0.00702 0.00094 -0.0446 0.5192 0.3420
-1.500 0.2258 0.00681 0.00093 -0.0447 0.5106 0.4217
-1.250 0.2537 0.00657 0.00094 -0.0448 0.5024 0.5156
-1.000 0.2809 0.00625 0.00095 -0.0448 0.4930 0.6411
-0.750 0.3072 0.00590 0.00099 -0.0445 0.4836 0.7708
-0.500 0.3308 0.00563 0.00104 -0.0433 0.4737 0.8827
-0.250 0.3561 0.00554 0.00106 -0.0424 0.4610 0.9599
0.000 0.3924 0.00560 0.00106 -0.0443 0.4443 0.9949
0.250 0.4220 0.00571 0.00109 -0.0447 0.4270 1.0000
0.500 0.4496 0.00584 0.00113 -0.0447 0.4086 1.0000
0.750 0.4773 0.00599 0.00119 -0.0447 0.3889 1.0000
1.000 0.5049 0.00615 0.00126 -0.0447 0.3682 1.0000
1.250 0.5324 0.00633 0.00134 -0.0447 0.3468 1.0000
1.500 0.5599 0.00651 0.00144 -0.0447 0.3260 1.0000
1.750 0.5873 0.00671 0.00154 -0.0447 0.3055 1.0000
2.000 0.6149 0.00688 0.00165 -0.0448 0.2886 1.0000
2.250 0.6423 0.00709 0.00178 -0.0448 0.2675 1.0000
2.500 0.6696 0.00731 0.00192 -0.0448 0.2488 1.0000
2.750 0.6967 0.00755 0.00208 -0.0449 0.2261 1.0000
3.000 0.7237 0.00782 0.00225 -0.0449 0.2039 1.0000
3.250 0.7508 0.00807 0.00243 -0.0449 0.1853 1.0000
3.500 0.7776 0.00836 0.00263 -0.0449 0.1652 1.0000
3.750 0.8044 0.00865 0.00285 -0.0449 0.1455 1.0000
4.000 0.8306 0.00902 0.00310 -0.0449 0.1208 1.0000
4.250 0.8571 0.00935 0.00336 -0.0449 0.1032 1.0000
4.500 0.8833 0.00971 0.00363 -0.0448 0.0864 1.0000
4.750 0.9095 0.01006 0.00391 -0.0448 0.0704 1.0000
5.000 0.9353 0.01047 0.00424 -0.0447 0.0542 1.0000
5.250 0.9608 0.01091 0.00461 -0.0446 0.0395 1.0000
5.500 0.9863 0.01133 0.00497 -0.0444 0.0291 1.0000
5.750 1.0118 0.01175 0.00536 -0.0443 0.0216 1.0000
6.000 1.0372 0.01217 0.00576 -0.0442 0.0163 1.0000
6.250 1.0624 0.01258 0.00617 -0.0440 0.0128 1.0000
6.500 1.0878 0.01297 0.00658 -0.0439 0.0107 1.0000
6.750 1.1126 0.01341 0.00703 -0.0437 0.0088 1.0000
7.000 1.1377 0.01381 0.00746 -0.0435 0.0079 1.0000
7.250 1.1623 0.01425 0.00794 -0.0433 0.0070 1.0000
7.500 1.1862 0.01478 0.00851 -0.0430 0.0061 1.0000
7.750 1.2104 0.01524 0.00902 -0.0427 0.0057 1.0000
8.000 1.2343 0.01573 0.00957 -0.0424 0.0053 1.0000
8.250 1.2576 0.01626 0.01015 -0.0421 0.0049 1.0000
8.500 1.2805 0.01683 0.01077 -0.0417 0.0046 1.0000
8.750 1.3026 0.01748 0.01148 -0.0412 0.0043 1.0000
9.000 1.3229 0.01833 0.01242 -0.0405 0.0040 1.0000
9.250 1.3443 0.01899 0.01316 -0.0399 0.0039 1.0000
9.500 1.3651 0.01967 0.01392 -0.0393 0.0038 1.0000
9.750 1.3853 0.02039 0.01472 -0.0386 0.0036 1.0000
10.000 1.4047 0.02115 0.01556 -0.0378 0.0035 1.0000
10.250 1.4232 0.02194 0.01644 -0.0370 0.0033 1.0000
10.500 1.4408 0.02279 0.01738 -0.0360 0.0032 1.0000
10.750 1.4571 0.02370 0.01838 -0.0350 0.0031 1.0000
11.000 1.4718 0.02467 0.01945 -0.0337 0.0030 1.0000
11.250 1.4847 0.02572 0.02059 -0.0323 0.0029 1.0000
11.500 1.4940 0.02682 0.02179 -0.0303 0.0029 1.0000
11.750 1.4995 0.02805 0.02313 -0.0280 0.0028 1.0000
12.000 1.5032 0.02950 0.02468 -0.0258 0.0027 1.0000
12.250 1.5055 0.03119 0.02649 -0.0240 0.0027 1.0000
12.500 1.5057 0.03326 0.02868 -0.0226 0.0027 1.0000
12.750 1.5037 0.03579 0.03135 -0.0218 0.0026 1.0000
13.000 1.5000 0.03882 0.03454 -0.0217 0.0026 1.0000
13.250 1.4940 0.04243 0.03829 -0.0222 0.0026 1.0000
13.500 1.4857 0.04673 0.04275 -0.0235 0.0025 1.0000
13.750 1.4751 0.05183 0.04800 -0.0257 0.0025 1.0000
14.000 1.4622 0.05761 0.05394 -0.0284 0.0025 1.0000
14.250 1.4467 0.06383 0.06032 -0.0313 0.0025 1.0000
14.500 1.4270 0.07084 0.06748 -0.0345 0.0025 1.0000
14.750 1.4071 0.07800 0.07477 -0.0377 0.0025 1.0000
15.000 1.3845 0.08583 0.08275 -0.0412 0.0025 1.0000
15.250 1.3625 0.09381 0.09086 -0.0449 0.0025 1.0000
15.500 1.3386 0.10242 0.09959 -0.0488 0.0025 1.0000
15.750 1.3144 0.11124 0.10854 -0.0528 0.0026 1.0000
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