AG11 (ag11-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG11 (ag11-il) Reynolds number: 500,000 Max Cl/Cd: 77.82 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag11-il-500000.txt Download as CSV file: xf-ag11-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5258 0.09818 0.09599 0.0111 1.0000 0.0098
-7.750 -0.5205 0.09439 0.09223 0.0083 1.0000 0.0098
-7.500 -0.5189 0.08917 0.08703 0.0055 1.0000 0.0100
-7.250 -0.5116 0.08557 0.08344 0.0045 1.0000 0.0102
-7.000 -0.5014 0.08189 0.07977 0.0018 1.0000 0.0104
-6.750 -0.4892 0.07809 0.07596 -0.0018 1.0000 0.0107
-6.500 -0.4748 0.07411 0.07197 -0.0059 1.0000 0.0112
-6.250 -0.4579 0.06986 0.06770 -0.0105 1.0000 0.0117
-6.000 -0.4388 0.06543 0.06322 -0.0152 1.0000 0.0121
-5.750 -0.4177 0.06094 0.05867 -0.0196 1.0000 0.0125
-5.500 -0.3943 0.05646 0.05411 -0.0236 1.0000 0.0130
-5.250 -0.3663 0.05198 0.04950 -0.0275 1.0000 0.0136
-5.000 -0.3361 0.04808 0.04542 -0.0302 1.0000 0.0140
-4.750 -0.3101 0.04450 0.04168 -0.0317 1.0000 0.0141
-4.500 -0.2850 0.04096 0.03796 -0.0327 1.0000 0.0142
-4.250 -0.2659 0.03500 0.03179 -0.0344 1.0000 0.0147
-4.000 -0.2446 0.03243 0.02912 -0.0348 1.0000 0.0152
-3.750 -0.2217 0.03010 0.02668 -0.0350 1.0000 0.0159
-3.500 -0.1976 0.02777 0.02419 -0.0348 1.0000 0.0168
-3.250 -0.1728 0.02549 0.02172 -0.0342 1.0000 0.0182
-3.000 -0.1456 0.02483 0.02080 -0.0326 1.0000 0.0203
-2.750 -0.1227 0.02085 0.01640 -0.0321 1.0000 0.0213
-2.500 -0.0926 0.01872 0.01418 -0.0334 0.9979 0.0229
-2.250 -0.0534 0.01714 0.01242 -0.0357 0.9939 0.0256
-2.000 -0.0138 0.01551 0.01039 -0.0375 0.9882 0.0311
-1.750 0.0267 0.01191 0.00629 -0.0379 0.9828 0.0147
-1.500 0.0630 0.01074 0.00502 -0.0391 0.9720 0.0140
-1.250 0.0969 0.00930 0.00347 -0.0400 0.9578 0.0151
-1.000 0.1268 0.00895 0.00314 -0.0401 0.9366 0.0186
-0.750 0.1533 0.00846 0.00257 -0.0393 0.9114 0.0195
-0.500 0.1787 0.00805 0.00202 -0.0382 0.8830 0.0214
-0.250 0.2045 0.00738 0.00153 -0.0373 0.8530 0.1238
0.000 0.2264 0.00492 0.00147 -0.0362 0.8228 1.0000
0.250 0.2524 0.00505 0.00137 -0.0354 0.7891 1.0000
0.500 0.2787 0.00521 0.00130 -0.0348 0.7551 1.0000
0.750 0.3053 0.00537 0.00126 -0.0343 0.7197 1.0000
1.000 0.3321 0.00555 0.00123 -0.0339 0.6852 1.0000
1.250 0.3591 0.00573 0.00123 -0.0336 0.6497 1.0000
1.500 0.3861 0.00593 0.00124 -0.0333 0.6135 1.0000
1.750 0.4133 0.00613 0.00127 -0.0331 0.5767 1.0000
2.000 0.4404 0.00635 0.00131 -0.0329 0.5389 1.0000
2.250 0.4675 0.00659 0.00137 -0.0327 0.4994 1.0000
2.500 0.4946 0.00685 0.00146 -0.0326 0.4599 1.0000
2.750 0.5217 0.00711 0.00155 -0.0325 0.4214 1.0000
3.000 0.5487 0.00740 0.00166 -0.0324 0.3837 1.0000
3.250 0.5758 0.00768 0.00179 -0.0323 0.3492 1.0000
3.500 0.6029 0.00797 0.00194 -0.0322 0.3171 1.0000
3.750 0.6300 0.00826 0.00211 -0.0321 0.2859 1.0000
4.000 0.6570 0.00855 0.00229 -0.0321 0.2588 1.0000
4.250 0.6840 0.00885 0.00248 -0.0320 0.2336 1.0000
4.500 0.7109 0.00916 0.00268 -0.0319 0.2087 1.0000
4.750 0.7377 0.00948 0.00294 -0.0318 0.1846 1.0000
5.000 0.7644 0.00984 0.00319 -0.0317 0.1631 1.0000
5.250 0.7911 0.01017 0.00346 -0.0316 0.1434 1.0000
5.500 0.8175 0.01057 0.00377 -0.0315 0.1247 1.0000
5.750 0.8438 0.01096 0.00413 -0.0314 0.1083 1.0000
6.000 0.8701 0.01138 0.00450 -0.0312 0.0947 1.0000
6.250 0.8960 0.01187 0.00494 -0.0310 0.0838 1.0000
6.500 0.9223 0.01224 0.00536 -0.0308 0.0767 1.0000
6.750 0.9479 0.01275 0.00588 -0.0306 0.0699 1.0000
7.000 0.9740 0.01314 0.00631 -0.0304 0.0647 1.0000
7.250 0.9984 0.01390 0.00708 -0.0300 0.0593 1.0000
7.500 1.0243 0.01427 0.00754 -0.0297 0.0565 1.0000
7.750 1.0498 0.01473 0.00807 -0.0295 0.0530 1.0000
8.000 1.0724 0.01576 0.00914 -0.0289 0.0483 1.0000
8.250 1.0978 0.01619 0.00967 -0.0286 0.0465 1.0000
8.500 1.1226 0.01670 0.01029 -0.0282 0.0440 1.0000
8.750 1.1473 0.01721 0.01087 -0.0279 0.0413 1.0000
9.000 1.1674 0.01863 0.01237 -0.0271 0.0378 1.0000
9.250 1.1913 0.01924 0.01310 -0.0267 0.0365 1.0000
9.500 1.2156 0.01972 0.01371 -0.0263 0.0344 1.0000
9.750 1.2391 0.02030 0.01439 -0.0259 0.0323 1.0000
10.000 1.2611 0.02109 0.01523 -0.0254 0.0301 1.0000
10.250 1.2785 0.02277 0.01707 -0.0244 0.0278 1.0000
10.500 1.3031 0.02297 0.01743 -0.0241 0.0261 1.0000
10.750 1.3272 0.02320 0.01771 -0.0239 0.0238 1.0000
11.000 1.3469 0.02411 0.01867 -0.0233 0.0214 1.0000
11.250 1.3653 0.02525 0.01997 -0.0224 0.0198 1.0000
11.500 1.3881 0.02561 0.02044 -0.0221 0.0178 1.0000
11.750 1.4093 0.02615 0.02100 -0.0217 0.0158 1.0000
12.000 1.4222 0.02780 0.02282 -0.0204 0.0140 1.0000
12.250 1.4413 0.02857 0.02375 -0.0198 0.0124 1.0000
12.500 1.4550 0.02988 0.02514 -0.0188 0.0107 1.0000
12.750 1.4605 0.03200 0.02747 -0.0171 0.0095 1.0000
13.000 1.4688 0.03360 0.02924 -0.0156 0.0084 1.0000
13.250 1.4697 0.03542 0.03119 -0.0136 0.0077 1.0000
13.500 1.4602 0.03837 0.03430 -0.0119 0.0072 1.0000
13.750 1.4439 0.04281 0.03894 -0.0123 0.0070 1.0000
14.000 1.4252 0.04883 0.04519 -0.0153 0.0068 1.0000
14.250 1.4087 0.05568 0.05225 -0.0198 0.0067 1.0000
14.500 1.3901 0.06358 0.06034 -0.0252 0.0067 1.0000
14.750 1.3703 0.07189 0.06883 -0.0305 0.0068 1.0000
15.000 1.3503 0.08024 0.07733 -0.0353 0.0069 1.0000
15.250 1.3312 0.08826 0.08549 -0.0396 0.0071 1.0000
15.500 1.3083 0.09694 0.09431 -0.0440 0.0073 1.0000
15.750 1.2825 0.10609 0.10361 -0.0485 0.0076 1.0000
16.000 1.2519 0.11626 0.11392 -0.0534 0.0080 1.0000
16.250 1.2214 0.12704 0.12483 -0.0589 0.0084 1.0000
16.500 1.1922 0.13803 0.13593 -0.0646 0.0089 1.0000
16.750 1.1648 0.14925 0.14723 -0.0705 0.0094 1.0000
17.000 1.1377 0.16100 0.15906 -0.0768 0.0098 1.0000
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Polar data table (+)
Polar graphs
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