AG11 (ag11-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG11 (ag11-il) Reynolds number: 100,000 Max Cl/Cd: 46.13 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag11-il-100000-n5.txt Download as CSV file: xf-ag11-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5155 0.10226 0.09741 0.0123 1.0000 0.0349
-7.750 -0.5105 0.09885 0.09404 0.0103 1.0000 0.0358
-7.500 -0.5056 0.09544 0.09067 0.0081 1.0000 0.0366
-7.250 -0.5001 0.09194 0.08722 0.0051 1.0000 0.0376
-7.000 -0.4904 0.08810 0.08341 0.0002 1.0000 0.0388
-6.750 -0.4744 0.08411 0.07940 -0.0085 1.0000 0.0403
-6.500 -0.4540 0.08019 0.07536 -0.0167 1.0000 0.0409
-6.250 -0.4350 0.07629 0.07129 -0.0216 1.0000 0.0412
-6.000 -0.4222 0.07094 0.06595 -0.0235 1.0000 0.0417
-5.750 -0.4134 0.06628 0.06138 -0.0227 1.0000 0.0427
-5.500 -0.3990 0.06260 0.05771 -0.0233 1.0000 0.0439
-5.250 -0.3810 0.05899 0.05404 -0.0250 1.0000 0.0455
-5.000 -0.3601 0.05533 0.05028 -0.0272 1.0000 0.0474
-4.750 -0.3239 0.05292 0.04730 -0.0321 1.0000 0.0541
-4.500 -0.3023 0.04851 0.04270 -0.0336 1.0000 0.0550
-4.250 -0.2835 0.04427 0.03847 -0.0341 1.0000 0.0560
-4.000 -0.2557 0.03888 0.03281 -0.0340 1.0000 0.0266
-3.750 -0.2296 0.03516 0.02877 -0.0346 1.0000 0.0236
-3.500 -0.1977 0.03191 0.02488 -0.0342 1.0000 0.0204
-3.000 -0.1496 0.02680 0.01934 -0.0344 1.0000 0.0229
-2.750 -0.1239 0.02489 0.01715 -0.0339 1.0000 0.0244
-2.500 -0.0974 0.02281 0.01470 -0.0332 1.0000 0.0241
-2.250 -0.0711 0.02098 0.01250 -0.0324 1.0000 0.0239
-2.000 -0.0451 0.01942 0.01068 -0.0316 1.0000 0.0241
-1.750 -0.0196 0.01811 0.00917 -0.0307 1.0000 0.0247
-1.500 0.0056 0.01698 0.00794 -0.0299 1.0000 0.0256
-1.250 0.0304 0.01612 0.00701 -0.0292 1.0000 0.0279
-1.000 0.0574 0.01523 0.00612 -0.0291 0.9982 0.0325
-0.750 0.0995 0.01439 0.00519 -0.0319 0.9856 0.0392
-0.500 0.1411 0.01359 0.00439 -0.0345 0.9714 0.0678
-0.250 0.1780 0.01054 0.00401 -0.0358 0.9579 1.0000
0.000 0.2169 0.01056 0.00374 -0.0378 0.9352 1.0000
0.250 0.2536 0.01059 0.00355 -0.0392 0.9096 1.0000
0.500 0.2865 0.01063 0.00341 -0.0397 0.8803 1.0000
0.750 0.3162 0.01070 0.00329 -0.0395 0.8480 1.0000
1.000 0.3436 0.01079 0.00321 -0.0387 0.8141 1.0000
1.250 0.3696 0.01092 0.00316 -0.0377 0.7780 1.0000
1.500 0.3950 0.01108 0.00313 -0.0367 0.7416 1.0000
1.750 0.4204 0.01127 0.00314 -0.0356 0.7040 1.0000
2.000 0.4460 0.01149 0.00317 -0.0348 0.6658 1.0000
2.250 0.4715 0.01174 0.00324 -0.0339 0.6269 1.0000
2.500 0.4969 0.01203 0.00335 -0.0331 0.5873 1.0000
2.750 0.5224 0.01233 0.00347 -0.0324 0.5470 1.0000
3.000 0.5479 0.01267 0.00362 -0.0318 0.5066 1.0000
3.250 0.5734 0.01303 0.00381 -0.0312 0.4670 1.0000
3.500 0.5988 0.01342 0.00403 -0.0307 0.4283 1.0000
3.750 0.6243 0.01384 0.00432 -0.0302 0.3906 1.0000
4.000 0.6497 0.01428 0.00461 -0.0298 0.3544 1.0000
4.250 0.6751 0.01475 0.00494 -0.0294 0.3202 1.0000
4.500 0.7004 0.01524 0.00531 -0.0291 0.2886 1.0000
4.750 0.7258 0.01574 0.00577 -0.0288 0.2581 1.0000
5.000 0.7510 0.01628 0.00622 -0.0285 0.2305 1.0000
5.250 0.7760 0.01685 0.00672 -0.0282 0.2052 1.0000
5.500 0.8011 0.01743 0.00727 -0.0278 0.1824 1.0000
5.750 0.8258 0.01808 0.00790 -0.0275 0.1617 1.0000
6.000 0.8505 0.01875 0.00858 -0.0272 0.1440 1.0000
6.250 0.8748 0.01949 0.00934 -0.0268 0.1300 1.0000
6.500 0.8988 0.02027 0.01014 -0.0263 0.1173 1.0000
6.750 0.9225 0.02109 0.01102 -0.0259 0.1063 1.0000
7.000 0.9458 0.02198 0.01196 -0.0254 0.0980 1.0000
7.250 0.9692 0.02295 0.01307 -0.0249 0.0911 1.0000
7.500 0.9917 0.02396 0.01410 -0.0243 0.0848 1.0000
7.750 1.0148 0.02495 0.01530 -0.0238 0.0783 1.0000
8.000 1.0370 0.02605 0.01652 -0.0232 0.0737 1.0000
8.250 1.0586 0.02746 0.01805 -0.0225 0.0701 1.0000
8.500 1.0806 0.02877 0.01964 -0.0219 0.0657 1.0000
8.750 1.1015 0.02994 0.02092 -0.0213 0.0615 1.0000
9.000 1.1213 0.03164 0.02280 -0.0206 0.0584 1.0000
9.250 1.1409 0.03355 0.02515 -0.0198 0.0556 1.0000
9.500 1.1593 0.03539 0.02729 -0.0190 0.0526 1.0000
9.750 1.1769 0.03685 0.02887 -0.0183 0.0496 1.0000
10.000 1.1916 0.03916 0.03143 -0.0174 0.0472 1.0000
10.250 1.2028 0.04207 0.03488 -0.0162 0.0452 1.0000
10.500 1.2105 0.04509 0.03838 -0.0151 0.0431 1.0000
10.750 1.2174 0.04757 0.04119 -0.0140 0.0410 1.0000
11.000 1.2262 0.04930 0.04304 -0.0131 0.0389 1.0000
11.250 1.2292 0.05218 0.04602 -0.0121 0.0375 1.0000
11.500 1.2173 0.05618 0.05044 -0.0107 0.0370 1.0000
11.750 1.1988 0.06045 0.05504 -0.0099 0.0367 1.0000
12.000 1.1777 0.06571 0.06058 -0.0115 0.0366 1.0000
12.250 1.1547 0.07235 0.06745 -0.0156 0.0367 1.0000
12.500 1.1299 0.08060 0.07587 -0.0217 0.0369 1.0000
12.750 1.1027 0.09051 0.08590 -0.0292 0.0373 1.0000
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Polar data table (+)
Polar graphs
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