AG04 (ag04-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG04 (ag04-il) Reynolds number: 100,000 Max Cl/Cd: 45.33 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag04-il-100000-n5.txt Download as CSV file: xf-ag04-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG04
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5765 0.11133 0.10650 0.0166 1.0000 0.0427
-8.750 -0.5735 0.10727 0.10247 0.0145 1.0000 0.0426
-8.500 -0.5718 0.10299 0.09824 0.0115 1.0000 0.0422
-8.250 -0.5659 0.09706 0.09228 0.0102 1.0000 0.0270
-8.000 -0.5625 0.09299 0.08825 0.0085 1.0000 0.0259
-7.750 -0.5601 0.08866 0.08397 0.0059 1.0000 0.0249
-7.500 -0.5567 0.08388 0.07924 0.0020 1.0000 0.0240
-7.250 -0.5499 0.07823 0.07362 -0.0037 1.0000 0.0230
-7.000 -0.5403 0.07136 0.06674 -0.0111 1.0000 0.0219
-6.500 -0.5066 0.05268 0.04759 -0.0280 1.0000 0.0194
-6.250 -0.4911 0.04661 0.04123 -0.0315 1.0000 0.0192
-6.000 -0.4728 0.04084 0.03501 -0.0342 1.0000 0.0191
-5.750 -0.4521 0.03572 0.02934 -0.0359 1.0000 0.0191
-5.500 -0.4293 0.03145 0.02444 -0.0368 1.0000 0.0192
-5.250 -0.4054 0.02773 0.02013 -0.0371 1.0000 0.0196
-5.000 -0.3817 0.02525 0.01732 -0.0373 1.0000 0.0216
-4.750 -0.3562 0.02363 0.01540 -0.0371 1.0000 0.0246
-4.500 -0.3298 0.02152 0.01288 -0.0367 1.0000 0.0266
-4.250 -0.3035 0.01974 0.01076 -0.0360 1.0000 0.0285
-4.000 -0.2782 0.01820 0.00915 -0.0356 1.0000 0.0330
-3.750 -0.2520 0.01721 0.00800 -0.0351 1.0000 0.0406
-3.500 -0.2264 0.01615 0.00688 -0.0346 1.0000 0.0524
-3.250 -0.2007 0.01520 0.00597 -0.0343 1.0000 0.0725
-3.000 -0.1750 0.01448 0.00531 -0.0339 1.0000 0.1049
-2.750 -0.1494 0.01385 0.00484 -0.0336 1.0000 0.1463
-2.500 -0.1240 0.01328 0.00446 -0.0332 1.0000 0.1972
-2.250 -0.0987 0.01275 0.00412 -0.0329 1.0000 0.2622
-2.000 -0.0737 0.01224 0.00390 -0.0325 1.0000 0.3451
-1.750 -0.0490 0.01172 0.00373 -0.0320 1.0000 0.4488
-1.500 -0.0254 0.01111 0.00361 -0.0311 1.0000 0.5843
-1.250 -0.0026 0.01018 0.00353 -0.0287 1.0000 0.8640
-1.000 0.0297 0.01010 0.00332 -0.0297 1.0000 1.0000
-0.750 0.0542 0.01016 0.00325 -0.0293 1.0000 1.0000
-0.500 0.0902 0.01024 0.00318 -0.0312 0.9899 1.0000
-0.250 0.1333 0.01031 0.00311 -0.0344 0.9717 1.0000
0.000 0.1741 0.01036 0.00306 -0.0370 0.9505 1.0000
0.250 0.2132 0.01041 0.00302 -0.0391 0.9266 1.0000
0.500 0.2484 0.01046 0.00299 -0.0403 0.8985 1.0000
0.750 0.2799 0.01052 0.00296 -0.0405 0.8669 1.0000
1.000 0.3086 0.01061 0.00295 -0.0401 0.8333 1.0000
1.250 0.3354 0.01072 0.00295 -0.0392 0.7982 1.0000
1.500 0.3612 0.01087 0.00297 -0.0382 0.7622 1.0000
1.750 0.3867 0.01105 0.00304 -0.0372 0.7255 1.0000
2.000 0.4122 0.01126 0.00311 -0.0362 0.6886 1.0000
2.250 0.4379 0.01150 0.00321 -0.0354 0.6509 1.0000
2.500 0.4635 0.01176 0.00334 -0.0346 0.6126 1.0000
2.750 0.4890 0.01204 0.00353 -0.0338 0.5741 1.0000
3.000 0.5145 0.01236 0.00371 -0.0331 0.5353 1.0000
3.250 0.5400 0.01270 0.00392 -0.0325 0.4967 1.0000
3.500 0.5656 0.01307 0.00418 -0.0319 0.4582 1.0000
3.750 0.5911 0.01346 0.00450 -0.0314 0.4209 1.0000
4.000 0.6166 0.01389 0.00482 -0.0309 0.3851 1.0000
4.250 0.6421 0.01433 0.00519 -0.0304 0.3501 1.0000
4.500 0.6674 0.01482 0.00559 -0.0300 0.3169 1.0000
4.750 0.6929 0.01531 0.00604 -0.0296 0.2844 1.0000
5.000 0.7181 0.01584 0.00657 -0.0292 0.2535 1.0000
5.250 0.7432 0.01641 0.00711 -0.0288 0.2235 1.0000
5.500 0.7681 0.01702 0.00769 -0.0285 0.1949 1.0000
5.750 0.7929 0.01769 0.00834 -0.0281 0.1674 1.0000
6.000 0.8173 0.01842 0.00905 -0.0277 0.1405 1.0000
6.250 0.8416 0.01923 0.00992 -0.0273 0.1161 1.0000
6.500 0.8653 0.02015 0.01085 -0.0268 0.0942 1.0000
6.750 0.8884 0.02120 0.01191 -0.0263 0.0763 1.0000
7.000 0.9107 0.02242 0.01314 -0.0257 0.0621 1.0000
7.250 0.9328 0.02367 0.01452 -0.0251 0.0511 1.0000
7.500 0.9544 0.02508 0.01609 -0.0243 0.0425 1.0000
7.750 0.9739 0.02687 0.01802 -0.0234 0.0369 1.0000
8.000 0.9951 0.02830 0.01971 -0.0226 0.0310 1.0000
8.250 1.0127 0.03048 0.02200 -0.0217 0.0278 1.0000
8.500 1.0313 0.03281 0.02470 -0.0206 0.0252 1.0000
8.750 1.0492 0.03479 0.02701 -0.0197 0.0219 1.0000
9.000 1.0647 0.03709 0.02955 -0.0188 0.0200 1.0000
9.250 1.0758 0.04028 0.03301 -0.0178 0.0189 1.0000
9.500 1.0819 0.04447 0.03762 -0.0166 0.0182 1.0000
9.750 1.0853 0.04839 0.04206 -0.0156 0.0178 1.0000
10.000 1.0827 0.05258 0.04673 -0.0147 0.0173 1.0000
10.250 1.0732 0.05696 0.05151 -0.0143 0.0169 1.0000
10.500 1.0573 0.06141 0.05624 -0.0145 0.0169 1.0000
10.750 1.0393 0.06696 0.06202 -0.0174 0.0170 1.0000
11.000 1.0209 0.07395 0.06919 -0.0228 0.0172 1.0000
11.250 1.0024 0.08234 0.07771 -0.0297 0.0176 1.0000
11.500 0.9839 0.09155 0.08699 -0.0366 0.0180 1.0000
11.750 0.9656 0.10104 0.09652 -0.0429 0.0183 1.0000
12.000 0.9460 0.11194 0.10748 -0.0495 0.0187 1.0000
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Polar data table (+)
Polar graphs
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