AG11 (ag11-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG11 (ag11-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.82 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag11-il-1000000.txt Download as CSV file: xf-ag11-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5426 0.10481 0.10322 0.0210 1.0000 0.0052
-8.250 -0.5377 0.10123 0.09965 0.0192 1.0000 0.0054
-8.000 -0.5328 0.09761 0.09605 0.0173 1.0000 0.0057
-7.750 -0.5277 0.09389 0.09234 0.0152 1.0000 0.0061
-7.500 -0.5217 0.08979 0.08826 0.0111 1.0000 0.0065
-7.250 -0.5114 0.08514 0.08362 0.0050 1.0000 0.0065
-7.000 -0.4976 0.08045 0.07892 -0.0006 1.0000 0.0066
-6.750 -0.4818 0.07569 0.07415 -0.0060 1.0000 0.0066
-6.500 -0.4643 0.07092 0.06935 -0.0111 1.0000 0.0066
-6.250 -0.4452 0.06618 0.06457 -0.0158 1.0000 0.0066
-6.000 -0.4309 0.05976 0.05809 -0.0208 1.0000 0.0068
-5.750 -0.4131 0.05632 0.05460 -0.0231 1.0000 0.0070
-5.500 -0.3926 0.05282 0.05105 -0.0256 1.0000 0.0072
-5.250 -0.3699 0.04905 0.04719 -0.0282 1.0000 0.0074
-5.000 -0.3458 0.04518 0.04322 -0.0306 1.0000 0.0076
-4.750 -0.3210 0.04140 0.03933 -0.0324 1.0000 0.0078
-4.500 -0.2956 0.03777 0.03556 -0.0337 1.0000 0.0081
-4.250 -0.2700 0.03428 0.03192 -0.0345 1.0000 0.0084
-4.000 -0.2440 0.03093 0.02838 -0.0348 1.0000 0.0089
-3.750 -0.2160 0.02796 0.02521 -0.0341 1.0000 0.0095
-3.500 -0.1879 0.02540 0.02244 -0.0339 0.9993 0.0097
-3.250 -0.1510 0.02234 0.01908 -0.0357 0.9957 0.0098
-3.000 -0.1180 0.01784 0.01423 -0.0379 0.9897 0.0105
-1.750 0.0333 0.00916 0.00424 -0.0375 0.9017 0.0083
-1.500 0.0593 0.00813 0.00298 -0.0364 0.8746 0.0080
-1.250 0.0856 0.00775 0.00244 -0.0357 0.8440 0.0090
-1.000 0.1125 0.00759 0.00214 -0.0352 0.8124 0.0099
-0.750 0.1398 0.00719 0.00156 -0.0349 0.7799 0.0110
-0.500 0.1672 0.00715 0.00141 -0.0346 0.7477 0.0130
-0.250 0.1951 0.00702 0.00110 -0.0344 0.7163 0.0157
0.000 0.2229 0.00659 0.00093 -0.0344 0.6838 0.1487
0.250 0.2477 0.00496 0.00095 -0.0347 0.6527 0.7546
0.500 0.2731 0.00446 0.00091 -0.0336 0.6217 1.0000
0.750 0.3007 0.00463 0.00089 -0.0335 0.5875 1.0000
1.000 0.3285 0.00479 0.00089 -0.0334 0.5540 1.0000
1.250 0.3562 0.00496 0.00090 -0.0333 0.5205 1.0000
1.500 0.3839 0.00516 0.00093 -0.0332 0.4846 1.0000
1.750 0.4116 0.00536 0.00096 -0.0332 0.4483 1.0000
2.000 0.4392 0.00557 0.00102 -0.0332 0.4145 1.0000
2.250 0.4669 0.00578 0.00108 -0.0331 0.3797 1.0000
2.500 0.4945 0.00601 0.00116 -0.0331 0.3468 1.0000
2.750 0.5221 0.00623 0.00125 -0.0331 0.3176 1.0000
3.000 0.5496 0.00646 0.00135 -0.0331 0.2883 1.0000
3.250 0.5772 0.00668 0.00146 -0.0331 0.2623 1.0000
3.500 0.6048 0.00689 0.00159 -0.0330 0.2401 1.0000
3.750 0.6323 0.00712 0.00172 -0.0330 0.2184 1.0000
4.000 0.6597 0.00736 0.00186 -0.0330 0.1958 1.0000
4.250 0.6870 0.00761 0.00201 -0.0330 0.1753 1.0000
4.500 0.7144 0.00785 0.00218 -0.0329 0.1576 1.0000
4.750 0.7416 0.00811 0.00238 -0.0329 0.1405 1.0000
5.000 0.7687 0.00839 0.00258 -0.0328 0.1240 1.0000
5.250 0.7957 0.00867 0.00279 -0.0328 0.1084 1.0000
5.500 0.8227 0.00896 0.00302 -0.0327 0.0951 1.0000
5.750 0.8496 0.00926 0.00328 -0.0326 0.0833 1.0000
6.000 0.8764 0.00958 0.00356 -0.0325 0.0735 1.0000
6.250 0.9033 0.00984 0.00382 -0.0324 0.0669 1.0000
6.500 0.9297 0.01022 0.00418 -0.0323 0.0594 1.0000
6.750 0.9566 0.01046 0.00445 -0.0322 0.0564 1.0000
7.000 0.9830 0.01081 0.00479 -0.0321 0.0519 1.0000
7.250 1.0091 0.01123 0.00524 -0.0319 0.0477 1.0000
7.500 1.0358 0.01146 0.00553 -0.0318 0.0456 1.0000
7.750 1.0620 0.01180 0.00589 -0.0316 0.0428 1.0000
8.000 1.0873 0.01233 0.00644 -0.0313 0.0388 1.0000
8.250 1.1131 0.01271 0.00689 -0.0311 0.0368 1.0000
8.500 1.1392 0.01301 0.00724 -0.0310 0.0353 1.0000
8.750 1.1649 0.01336 0.00764 -0.0308 0.0331 1.0000
9.000 1.1898 0.01388 0.00817 -0.0305 0.0302 1.0000
9.250 1.2135 0.01461 0.00900 -0.0300 0.0280 1.0000
9.500 1.2395 0.01484 0.00928 -0.0299 0.0269 1.0000
9.750 1.2652 0.01508 0.00954 -0.0298 0.0248 1.0000
10.000 1.2893 0.01561 0.01006 -0.0295 0.0219 1.0000
10.250 1.3131 0.01620 0.01074 -0.0291 0.0202 1.0000
10.500 1.3379 0.01655 0.01116 -0.0289 0.0190 1.0000
10.750 1.3619 0.01702 0.01166 -0.0285 0.0173 1.0000
11.000 1.3838 0.01784 0.01252 -0.0280 0.0149 1.0000
11.250 1.4074 0.01833 0.01309 -0.0276 0.0139 1.0000
11.500 1.4304 0.01887 0.01368 -0.0273 0.0123 1.0000
11.750 1.4505 0.01986 0.01471 -0.0266 0.0100 1.0000
12.000 1.4726 0.02045 0.01541 -0.0261 0.0089 1.0000
12.250 1.4904 0.02168 0.01669 -0.0252 0.0067 1.0000
12.500 1.5096 0.02261 0.01772 -0.0245 0.0056 1.0000
12.750 1.5236 0.02422 0.01946 -0.0232 0.0043 1.0000
13.000 1.5403 0.02532 0.02069 -0.0223 0.0037 1.0000
13.250 1.5534 0.02677 0.02226 -0.0210 0.0032 1.0000
13.500 1.5569 0.02921 0.02492 -0.0190 0.0027 1.0000
13.750 1.5666 0.03068 0.02655 -0.0176 0.0026 1.0000
14.000 1.5705 0.03237 0.02839 -0.0155 0.0025 1.0000
14.250 1.5676 0.03434 0.03052 -0.0131 0.0024 1.0000
14.500 1.5618 0.03690 0.03326 -0.0117 0.0023 1.0000
14.750 1.5534 0.04030 0.03682 -0.0117 0.0022 1.0000
15.000 1.5422 0.04484 0.04154 -0.0134 0.0022 1.0000
15.250 1.5271 0.05095 0.04784 -0.0171 0.0022 1.0000
15.500 1.5047 0.05928 0.05638 -0.0229 0.0022 1.0000
15.750 1.4721 0.07020 0.06751 -0.0301 0.0022 1.0000
16.000 1.4262 0.08367 0.08115 -0.0378 0.0024 1.0000
16.250 1.3693 0.09892 0.09657 -0.0456 0.0026 1.0000
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Polar data table (+)
Polar graphs
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