AG36 (ag36-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG36 (ag36-il) Reynolds number: 100,000 Max Cl/Cd: 50.98 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag36-il-100000-n5.txt Download as CSV file: xf-ag36-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG36
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5039 0.09202 0.08714 -0.0109 1.0000 0.0384
-9.500 -0.5011 0.08797 0.08313 -0.0120 1.0000 0.0358
-9.250 -0.5079 0.07849 0.07369 -0.0235 1.0000 0.0299
-9.000 -0.5023 0.07420 0.06940 -0.0259 1.0000 0.0294
-8.750 -0.4960 0.06923 0.06440 -0.0294 1.0000 0.0288
-8.500 -0.4884 0.06382 0.05892 -0.0332 1.0000 0.0283
-8.250 -0.4796 0.05812 0.05309 -0.0366 1.0000 0.0278
-8.000 -0.4694 0.05235 0.04710 -0.0394 1.0000 0.0273
-7.750 -0.4574 0.04676 0.04120 -0.0412 1.0000 0.0270
-7.500 -0.4432 0.04181 0.03585 -0.0422 1.0000 0.0277
-7.250 -0.4268 0.03740 0.03091 -0.0424 1.0000 0.0289
-7.000 -0.4085 0.03367 0.02659 -0.0420 1.0000 0.0295
-6.750 -0.3888 0.03050 0.02291 -0.0413 1.0000 0.0298
-6.500 -0.3675 0.02788 0.01977 -0.0405 1.0000 0.0302
-6.250 -0.3457 0.02544 0.01695 -0.0397 1.0000 0.0308
-6.000 -0.3236 0.02361 0.01493 -0.0389 1.0000 0.0320
-5.750 -0.3011 0.02252 0.01370 -0.0381 1.0000 0.0347
-5.500 -0.2778 0.02132 0.01227 -0.0372 1.0000 0.0375
-5.250 -0.2540 0.02006 0.01078 -0.0362 1.0000 0.0393
-5.000 -0.2307 0.01883 0.00946 -0.0354 1.0000 0.0414
-4.750 -0.2078 0.01806 0.00872 -0.0346 1.0000 0.0462
-4.500 -0.1843 0.01738 0.00793 -0.0338 1.0000 0.0513
-4.250 -0.1559 0.01654 0.00710 -0.0342 0.9975 0.0579
-4.000 -0.1179 0.01582 0.00637 -0.0364 0.9902 0.0735
-3.750 -0.0791 0.01502 0.00572 -0.0388 0.9831 0.1089
-3.500 -0.0431 0.01407 0.00530 -0.0409 0.9741 0.2237
-3.250 -0.0076 0.01309 0.00510 -0.0430 0.9655 0.4201
-3.000 0.0210 0.01191 0.00507 -0.0424 0.9566 0.7194
-2.750 0.0744 0.01143 0.00485 -0.0461 0.9486 1.0000
-2.500 0.1107 0.01141 0.00462 -0.0478 0.9337 1.0000
-2.250 0.1455 0.01138 0.00441 -0.0491 0.9171 1.0000
-2.000 0.1791 0.01136 0.00421 -0.0500 0.8988 1.0000
-1.750 0.2101 0.01134 0.00404 -0.0503 0.8774 1.0000
-1.500 0.2415 0.01132 0.00387 -0.0506 0.8566 1.0000
-1.250 0.2701 0.01135 0.00373 -0.0503 0.8335 1.0000
-1.000 0.2979 0.01140 0.00363 -0.0498 0.8106 1.0000
-0.750 0.3246 0.01148 0.00358 -0.0492 0.7863 1.0000
-0.500 0.3511 0.01159 0.00356 -0.0486 0.7620 1.0000
-0.250 0.3775 0.01172 0.00356 -0.0480 0.7377 1.0000
0.000 0.4036 0.01186 0.00359 -0.0474 0.7124 1.0000
0.250 0.4297 0.01200 0.00363 -0.0469 0.6868 1.0000
0.500 0.4558 0.01216 0.00370 -0.0463 0.6612 1.0000
0.750 0.4817 0.01234 0.00374 -0.0457 0.6391 1.0000
1.000 0.5078 0.01256 0.00383 -0.0452 0.6185 1.0000
1.250 0.5338 0.01281 0.00396 -0.0447 0.5993 1.0000
1.500 0.5598 0.01309 0.00416 -0.0442 0.5810 1.0000
1.750 0.5859 0.01337 0.00439 -0.0438 0.5625 1.0000
2.000 0.6120 0.01365 0.00463 -0.0434 0.5439 1.0000
2.250 0.6379 0.01394 0.00489 -0.0431 0.5255 1.0000
2.500 0.6638 0.01423 0.00518 -0.0427 0.5071 1.0000
2.750 0.6897 0.01449 0.00547 -0.0423 0.4868 1.0000
3.000 0.7154 0.01475 0.00576 -0.0419 0.4655 1.0000
3.250 0.7410 0.01501 0.00606 -0.0416 0.4422 1.0000
3.500 0.7663 0.01531 0.00638 -0.0411 0.4178 1.0000
3.750 0.7912 0.01564 0.00669 -0.0407 0.3915 1.0000
4.000 0.8158 0.01603 0.00706 -0.0402 0.3638 1.0000
4.250 0.8401 0.01648 0.00747 -0.0397 0.3349 1.0000
4.500 0.8640 0.01700 0.00798 -0.0392 0.3060 1.0000
4.750 0.8876 0.01756 0.00852 -0.0387 0.2764 1.0000
5.000 0.9108 0.01819 0.00911 -0.0382 0.2466 1.0000
5.250 0.9335 0.01887 0.00977 -0.0377 0.2177 1.0000
5.500 0.9558 0.01962 0.01051 -0.0371 0.1895 1.0000
5.750 0.9775 0.02045 0.01129 -0.0366 0.1612 1.0000
6.000 0.9987 0.02135 0.01214 -0.0360 0.1334 1.0000
6.250 1.0192 0.02233 0.01308 -0.0354 0.1074 1.0000
6.500 1.0387 0.02347 0.01419 -0.0346 0.0837 1.0000
6.750 1.0571 0.02475 0.01544 -0.0337 0.0641 1.0000
7.000 1.0737 0.02622 0.01689 -0.0326 0.0511 1.0000
7.250 1.0902 0.02766 0.01843 -0.0314 0.0421 1.0000
7.500 1.1044 0.02932 0.02021 -0.0300 0.0369 1.0000
7.750 1.1191 0.03082 0.02182 -0.0288 0.0322 1.0000
8.000 1.1306 0.03268 0.02382 -0.0272 0.0293 1.0000
8.250 1.1430 0.03451 0.02588 -0.0256 0.0273 1.0000
8.500 1.1544 0.03636 0.02790 -0.0241 0.0254 1.0000
8.750 1.1636 0.03822 0.02985 -0.0226 0.0237 1.0000
9.000 1.1700 0.04053 0.03229 -0.0209 0.0223 1.0000
9.250 1.1767 0.04266 0.03472 -0.0191 0.0211 1.0000
9.500 1.1801 0.04510 0.03742 -0.0171 0.0204 1.0000
9.750 1.1812 0.04778 0.04036 -0.0154 0.0198 1.0000
10.000 1.1796 0.05072 0.04355 -0.0140 0.0193 1.0000
10.250 1.1755 0.05396 0.04704 -0.0131 0.0190 1.0000
10.500 1.1688 0.05759 0.05093 -0.0128 0.0187 1.0000
10.750 1.1597 0.06171 0.05534 -0.0132 0.0185 1.0000
11.000 1.1483 0.06641 0.06028 -0.0145 0.0184 1.0000
11.250 1.1346 0.07181 0.06593 -0.0167 0.0183 1.0000
11.500 1.1183 0.07807 0.07243 -0.0199 0.0183 1.0000
11.750 1.0990 0.08532 0.07987 -0.0240 0.0184 1.0000
12.000 1.0766 0.09372 0.08850 -0.0292 0.0186 1.0000
12.250 1.0501 0.10374 0.09871 -0.0355 0.0189 1.0000
12.500 1.0164 0.11663 0.11179 -0.0436 0.0195 1.0000
12.750 0.9793 0.13214 0.12738 -0.0524 0.0203 1.0000
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Polar data table (+)
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