AG11 (ag11-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG11 (ag11-il) Reynolds number: 200,000 Max Cl/Cd: 58.11 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag11-il-200000-n5.txt Download as CSV file: xf-ag11-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5201 0.09986 0.09640 0.0142 1.0000 0.0173
-7.750 -0.5150 0.09636 0.09293 0.0122 1.0000 0.0177
-7.500 -0.5100 0.09285 0.08945 0.0099 1.0000 0.0180
-7.250 -0.5045 0.08925 0.08589 0.0069 1.0000 0.0184
-7.000 -0.4943 0.08521 0.08186 0.0024 1.0000 0.0189
-6.750 -0.4804 0.08091 0.07756 -0.0034 1.0000 0.0194
-6.500 -0.4609 0.07633 0.07293 -0.0107 1.0000 0.0199
-6.250 -0.4392 0.07185 0.06837 -0.0168 1.0000 0.0202
-6.000 -0.4182 0.06756 0.06398 -0.0211 1.0000 0.0204
-5.750 -0.3973 0.06343 0.05975 -0.0242 1.0000 0.0204
-5.500 -0.3761 0.05938 0.05557 -0.0268 1.0000 0.0205
-5.000 -0.3427 0.04944 0.04548 -0.0307 1.0000 0.0213
-4.750 -0.3236 0.04607 0.04204 -0.0317 1.0000 0.0219
-4.500 -0.3017 0.04288 0.03873 -0.0328 1.0000 0.0226
-4.250 -0.2779 0.03970 0.03540 -0.0337 1.0000 0.0233
-4.000 -0.2529 0.03657 0.03206 -0.0345 1.0000 0.0239
-3.750 -0.2271 0.03346 0.02871 -0.0349 1.0000 0.0241
-3.500 -0.1960 0.02827 0.02299 -0.0344 1.0000 0.0133
-3.250 -0.1709 0.02552 0.01997 -0.0342 1.0000 0.0125
-3.000 -0.1449 0.02281 0.01691 -0.0336 1.0000 0.0118
-2.750 -0.1187 0.02029 0.01401 -0.0328 1.0000 0.0113
-2.500 -0.0926 0.01818 0.01153 -0.0320 1.0000 0.0111
-2.250 -0.0606 0.01638 0.00938 -0.0324 0.9964 0.0113
-2.000 -0.0228 0.01499 0.00772 -0.0340 0.9874 0.0126
-1.750 0.0140 0.01385 0.00641 -0.0356 0.9761 0.0152
-1.500 0.0501 0.01278 0.00527 -0.0371 0.9625 0.0160
-1.250 0.0857 0.01193 0.00436 -0.0384 0.9459 0.0172
-1.000 0.1198 0.01129 0.00365 -0.0394 0.9255 0.0191
-0.750 0.1512 0.01079 0.00308 -0.0397 0.9007 0.0246
-0.500 0.1801 0.01040 0.00262 -0.0394 0.8726 0.0414
-0.250 0.1952 0.00778 0.00250 -0.0371 0.8446 0.7751
0.000 0.2306 0.00749 0.00225 -0.0375 0.8115 1.0000
0.250 0.2561 0.00761 0.00211 -0.0365 0.7769 1.0000
0.500 0.2816 0.00776 0.00200 -0.0357 0.7424 1.0000
0.750 0.3075 0.00792 0.00193 -0.0349 0.7075 1.0000
1.000 0.3335 0.00811 0.00188 -0.0343 0.6727 1.0000
1.250 0.3597 0.00831 0.00187 -0.0337 0.6374 1.0000
1.500 0.3859 0.00854 0.00187 -0.0332 0.6013 1.0000
1.750 0.4123 0.00877 0.00190 -0.0328 0.5643 1.0000
2.000 0.4387 0.00902 0.00195 -0.0324 0.5277 1.0000
2.250 0.4652 0.00928 0.00202 -0.0320 0.4904 1.0000
2.500 0.4917 0.00956 0.00213 -0.0318 0.4541 1.0000
2.750 0.5182 0.00986 0.00225 -0.0315 0.4184 1.0000
3.000 0.5447 0.01017 0.00239 -0.0313 0.3835 1.0000
3.250 0.5712 0.01049 0.00256 -0.0311 0.3500 1.0000
3.500 0.5976 0.01083 0.00275 -0.0309 0.3182 1.0000
3.750 0.6241 0.01118 0.00299 -0.0307 0.2881 1.0000
4.000 0.6505 0.01153 0.00322 -0.0306 0.2598 1.0000
4.250 0.6768 0.01190 0.00348 -0.0304 0.2337 1.0000
4.500 0.7032 0.01226 0.00375 -0.0303 0.2101 1.0000
4.750 0.7295 0.01265 0.00410 -0.0301 0.1874 1.0000
5.000 0.7556 0.01306 0.00444 -0.0299 0.1665 1.0000
5.250 0.7817 0.01347 0.00481 -0.0298 0.1495 1.0000
5.500 0.8077 0.01390 0.00521 -0.0296 0.1329 1.0000
5.750 0.8334 0.01436 0.00567 -0.0294 0.1173 1.0000
6.000 0.8591 0.01484 0.00614 -0.0292 0.1043 1.0000
6.250 0.8845 0.01536 0.00666 -0.0289 0.0944 1.0000
6.500 0.9097 0.01591 0.00722 -0.0286 0.0857 1.0000
6.750 0.9350 0.01644 0.00784 -0.0284 0.0782 1.0000
7.000 0.9594 0.01711 0.00850 -0.0280 0.0715 1.0000
7.250 0.9844 0.01767 0.00919 -0.0277 0.0668 1.0000
7.500 1.0086 0.01833 0.00993 -0.0273 0.0623 1.0000
7.750 1.0322 0.01913 0.01080 -0.0269 0.0583 1.0000
8.000 1.0564 0.01976 0.01159 -0.0265 0.0543 1.0000
8.250 1.0798 0.02052 0.01244 -0.0260 0.0510 1.0000
8.500 1.1011 0.02166 0.01362 -0.0254 0.0480 1.0000
8.750 1.1243 0.02245 0.01462 -0.0249 0.0458 1.0000
9.000 1.1470 0.02327 0.01565 -0.0243 0.0428 1.0000
9.250 1.1689 0.02415 0.01665 -0.0238 0.0402 1.0000
9.500 1.1882 0.02550 0.01808 -0.0231 0.0379 1.0000
9.750 1.2087 0.02665 0.01946 -0.0223 0.0361 1.0000
10.000 1.2291 0.02771 0.02076 -0.0216 0.0337 1.0000
10.250 1.2484 0.02884 0.02209 -0.0209 0.0317 1.0000
10.500 1.2666 0.02996 0.02335 -0.0201 0.0298 1.0000
10.750 1.2809 0.03171 0.02528 -0.0191 0.0279 1.0000
11.000 1.2968 0.03317 0.02707 -0.0181 0.0263 1.0000
11.250 1.3106 0.03475 0.02892 -0.0171 0.0245 1.0000
11.500 1.3242 0.03600 0.03035 -0.0162 0.0227 1.0000
11.750 1.3345 0.03741 0.03188 -0.0151 0.0212 1.0000
12.000 1.3379 0.03972 0.03443 -0.0136 0.0200 1.0000
12.250 1.3379 0.04193 0.03694 -0.0118 0.0189 1.0000
12.500 1.3356 0.04435 0.03962 -0.0107 0.0178 1.0000
12.750 1.3327 0.04708 0.04254 -0.0105 0.0168 1.0000
13.000 1.3283 0.05042 0.04606 -0.0116 0.0161 1.0000
13.250 1.3201 0.05490 0.05072 -0.0140 0.0156 1.0000
13.500 1.3075 0.06076 0.05677 -0.0179 0.0153 1.0000
13.750 1.2902 0.06810 0.06432 -0.0229 0.0153 1.0000
14.000 1.2659 0.07726 0.07373 -0.0289 0.0155 1.0000
14.250 1.2183 0.09153 0.08830 -0.0374 0.0168 1.0000
14.500 1.1596 0.10880 0.10574 -0.0472 0.0189 1.0000
14.750 1.1192 0.12253 0.11951 -0.0546 0.0199 1.0000
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Polar data table (+)
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