AG08 (ag08-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG08 (ag08-il) Reynolds number: 50,000 Max Cl/Cd: 33.77 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag08-il-50000-n5.txt Download as CSV file: xf-ag08-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG08
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5689 0.11425 0.10739 0.0167 1.0000 0.0969
-8.500 -0.5663 0.11070 0.10390 0.0146 1.0000 0.0984
-8.000 -0.5639 0.10369 0.09702 0.0089 1.0000 0.1004
-7.750 -0.5538 0.09567 0.08896 0.0057 1.0000 0.0566
-7.250 -0.5415 0.08442 0.07775 -0.0069 1.0000 0.0477
-7.000 -0.5316 0.07990 0.07323 -0.0094 1.0000 0.0467
-6.750 -0.5203 0.07496 0.06828 -0.0131 1.0000 0.0458
-6.500 -0.5070 0.06968 0.06294 -0.0174 1.0000 0.0450
-6.250 -0.4916 0.06409 0.05725 -0.0219 1.0000 0.0444
-6.000 -0.4737 0.05835 0.05132 -0.0265 1.0000 0.0449
-5.750 -0.4535 0.05248 0.04512 -0.0308 1.0000 0.0461
-5.500 -0.4311 0.04664 0.03877 -0.0344 1.0000 0.0474
-5.250 -0.4073 0.04154 0.03301 -0.0366 1.0000 0.0481
-5.000 -0.3822 0.03703 0.02779 -0.0379 1.0000 0.0488
-4.750 -0.3585 0.03363 0.02411 -0.0384 1.0000 0.0507
-4.500 -0.3336 0.03142 0.02161 -0.0385 1.0000 0.0563
-4.250 -0.3054 0.02850 0.01787 -0.0385 1.0000 0.0615
-4.000 -0.2799 0.02626 0.01548 -0.0382 1.0000 0.0659
-3.750 -0.2531 0.02454 0.01338 -0.0378 1.0000 0.0761
-3.500 -0.2268 0.02298 0.01157 -0.0373 1.0000 0.0862
-3.250 -0.2003 0.02169 0.01008 -0.0367 1.0000 0.1019
-3.000 -0.1745 0.02049 0.00889 -0.0362 1.0000 0.1199
-2.750 -0.1479 0.01951 0.00791 -0.0358 1.0000 0.1498
-2.500 -0.1216 0.01853 0.00701 -0.0355 1.0000 0.1893
-2.250 -0.0957 0.01758 0.00627 -0.0352 1.0000 0.2525
-2.000 -0.0712 0.01656 0.00577 -0.0348 1.0000 0.3611
-1.750 -0.0512 0.01525 0.00538 -0.0330 1.0000 0.5560
-1.500 -0.0196 0.01402 0.00488 -0.0321 1.0000 1.0000
-1.250 0.0056 0.01402 0.00451 -0.0317 1.0000 1.0000
-1.000 0.0304 0.01404 0.00426 -0.0311 1.0000 1.0000
-0.750 0.0550 0.01408 0.00409 -0.0306 1.0000 1.0000
-0.500 0.0793 0.01414 0.00398 -0.0301 1.0000 1.0000
-0.250 0.1036 0.01422 0.00392 -0.0296 1.0000 1.0000
0.000 0.1277 0.01432 0.00389 -0.0291 1.0000 1.0000
0.250 0.1515 0.01445 0.00395 -0.0286 1.0000 1.0000
0.500 0.1751 0.01461 0.00406 -0.0282 1.0000 1.0000
0.750 0.1984 0.01480 0.00424 -0.0278 1.0000 1.0000
1.000 0.2215 0.01504 0.00448 -0.0275 1.0000 1.0000
1.250 0.2654 0.01531 0.00478 -0.0313 0.9816 1.0000
1.500 0.3168 0.01550 0.00504 -0.0361 0.9526 1.0000
1.750 0.3625 0.01562 0.00528 -0.0394 0.9182 1.0000
2.000 0.4038 0.01571 0.00545 -0.0414 0.8788 1.0000
2.250 0.4403 0.01581 0.00559 -0.0422 0.8345 1.0000
2.500 0.4715 0.01595 0.00572 -0.0416 0.7866 1.0000
2.750 0.4983 0.01618 0.00593 -0.0403 0.7355 1.0000
3.000 0.5230 0.01648 0.00613 -0.0386 0.6836 1.0000
3.250 0.5467 0.01688 0.00639 -0.0368 0.6323 1.0000
3.500 0.5703 0.01734 0.00671 -0.0353 0.5818 1.0000
3.750 0.5938 0.01786 0.00716 -0.0339 0.5337 1.0000
4.000 0.6175 0.01844 0.00762 -0.0327 0.4880 1.0000
4.250 0.6414 0.01906 0.00815 -0.0316 0.4449 1.0000
4.500 0.6653 0.01972 0.00875 -0.0307 0.4039 1.0000
4.750 0.6895 0.02042 0.00942 -0.0299 0.3645 1.0000
5.000 0.7138 0.02118 0.01020 -0.0293 0.3265 1.0000
5.250 0.7380 0.02198 0.01102 -0.0286 0.2884 1.0000
5.500 0.7619 0.02284 0.01191 -0.0280 0.2504 1.0000
5.750 0.7852 0.02381 0.01287 -0.0274 0.2131 1.0000
6.000 0.8078 0.02492 0.01395 -0.0267 0.1769 1.0000
6.250 0.8304 0.02622 0.01533 -0.0261 0.1416 1.0000
6.500 0.8521 0.02777 0.01688 -0.0254 0.1130 1.0000
6.750 0.8734 0.02958 0.01874 -0.0245 0.0913 1.0000
7.000 0.8941 0.03144 0.02071 -0.0237 0.0742 1.0000
7.250 0.9151 0.03378 0.02327 -0.0226 0.0643 1.0000
7.500 0.9345 0.03606 0.02568 -0.0218 0.0559 1.0000
7.750 0.9542 0.03866 0.02869 -0.0208 0.0495 1.0000
8.000 0.9716 0.04170 0.03193 -0.0200 0.0463 1.0000
8.250 0.9867 0.04556 0.03650 -0.0190 0.0433 1.0000
8.500 0.9980 0.04933 0.04084 -0.0183 0.0400 1.0000
8.750 1.0069 0.05290 0.04479 -0.0177 0.0376 1.0000
9.000 1.0115 0.05710 0.04937 -0.0172 0.0365 1.0000
9.250 1.0113 0.06169 0.05430 -0.0170 0.0360 1.0000
9.500 1.0052 0.06664 0.05957 -0.0173 0.0357 1.0000
9.750 0.9917 0.07203 0.06526 -0.0184 0.0358 1.0000
10.000 0.9672 0.07860 0.07208 -0.0217 0.0364 1.0000
10.250 0.9324 0.09054 0.08417 -0.0326 0.0382 1.0000
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Polar data table (+)
Polar graphs
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