AG08 (ag08-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG08 (ag08-il) Reynolds number: 200,000 Max Cl/Cd: 58.34 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag08-il-200000.txt Download as CSV file: xf-ag08-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4578 0.08433 0.08113 0.0029 1.0000 0.0432
-7.750 -0.4582 0.08026 0.07707 0.0012 1.0000 0.0447
-7.500 -0.5591 0.08709 0.08381 0.0042 1.0000 0.0389
-7.250 -0.5493 0.08410 0.08083 0.0035 1.0000 0.0413
-7.000 -0.5388 0.07982 0.07655 -0.0009 1.0000 0.0435
-6.750 -0.5244 0.07461 0.07133 -0.0080 1.0000 0.0460
-6.500 -0.4917 0.06674 0.06317 -0.0253 1.0000 0.0486
-6.250 -0.4830 0.05924 0.05563 -0.0285 1.0000 0.0497
-6.000 -0.4704 0.05622 0.05263 -0.0276 1.0000 0.0511
-5.750 -0.4529 0.05295 0.04932 -0.0286 1.0000 0.0531
-5.500 -0.4307 0.04855 0.04477 -0.0316 1.0000 0.0568
-5.250 -0.4032 0.04137 0.03701 -0.0372 1.0000 0.0632
-5.000 -0.3750 0.03001 0.02477 -0.0388 1.0000 0.0351
-4.750 -0.3502 0.02521 0.01939 -0.0392 1.0000 0.0341
-4.500 -0.3228 0.02314 0.01675 -0.0388 1.0000 0.0364
-4.250 -0.2963 0.02025 0.01334 -0.0384 1.0000 0.0366
-4.000 -0.2703 0.01680 0.00945 -0.0381 1.0000 0.0386
-3.750 -0.2443 0.01580 0.00838 -0.0377 1.0000 0.0440
-3.500 -0.2173 0.01496 0.00727 -0.0370 1.0000 0.0488
-3.250 -0.1917 0.01342 0.00576 -0.0365 1.0000 0.0570
-3.000 -0.1658 0.01257 0.00491 -0.0360 1.0000 0.0690
-2.750 -0.1398 0.01187 0.00421 -0.0355 1.0000 0.0857
-2.500 -0.1139 0.01117 0.00361 -0.0351 1.0000 0.1094
-2.250 -0.0880 0.01061 0.00318 -0.0347 1.0000 0.1458
-2.000 -0.0622 0.01000 0.00286 -0.0345 1.0000 0.2066
-1.750 -0.0365 0.00934 0.00270 -0.0344 1.0000 0.3237
-1.500 -0.0115 0.00855 0.00260 -0.0341 1.0000 0.4974
-1.250 0.0148 0.00715 0.00251 -0.0326 1.0000 1.0000
-1.000 0.0404 0.00719 0.00240 -0.0321 1.0000 1.0000
-0.750 0.0659 0.00724 0.00234 -0.0317 1.0000 1.0000
-0.500 0.0915 0.00731 0.00232 -0.0314 1.0000 1.0000
-0.250 0.1170 0.00740 0.00233 -0.0311 1.0000 1.0000
0.000 0.1423 0.00752 0.00239 -0.0308 1.0000 1.0000
0.250 0.1785 0.00762 0.00245 -0.0328 0.9947 1.0000
0.500 0.2285 0.00763 0.00244 -0.0375 0.9804 1.0000
0.750 0.2738 0.00759 0.00240 -0.0409 0.9616 1.0000
1.000 0.3146 0.00755 0.00234 -0.0432 0.9376 1.0000
1.250 0.3484 0.00752 0.00229 -0.0438 0.9057 1.0000
1.500 0.3762 0.00754 0.00226 -0.0430 0.8671 1.0000
1.750 0.4008 0.00764 0.00224 -0.0415 0.8229 1.0000
2.000 0.4246 0.00783 0.00225 -0.0399 0.7747 1.0000
2.250 0.4486 0.00807 0.00229 -0.0385 0.7223 1.0000
2.500 0.4730 0.00838 0.00237 -0.0373 0.6683 1.0000
2.750 0.4978 0.00872 0.00251 -0.0364 0.6136 1.0000
3.000 0.5228 0.00910 0.00266 -0.0356 0.5597 1.0000
3.250 0.5480 0.00951 0.00284 -0.0349 0.5089 1.0000
3.500 0.5736 0.00990 0.00306 -0.0344 0.4616 1.0000
3.750 0.5993 0.01032 0.00334 -0.0339 0.4183 1.0000
4.000 0.6250 0.01074 0.00362 -0.0335 0.3783 1.0000
4.250 0.6508 0.01118 0.00393 -0.0332 0.3412 1.0000
4.500 0.6767 0.01160 0.00426 -0.0328 0.3050 1.0000
4.750 0.7025 0.01206 0.00465 -0.0325 0.2704 1.0000
5.000 0.7283 0.01252 0.00505 -0.0322 0.2352 1.0000
5.250 0.7538 0.01305 0.00548 -0.0319 0.1997 1.0000
5.500 0.7790 0.01366 0.00597 -0.0316 0.1630 1.0000
5.750 0.8040 0.01436 0.00655 -0.0313 0.1248 1.0000
6.000 0.8283 0.01528 0.00737 -0.0308 0.0879 1.0000
6.250 0.8514 0.01657 0.00852 -0.0302 0.0600 1.0000
6.500 0.8741 0.01802 0.00997 -0.0294 0.0443 1.0000
6.750 0.8969 0.01945 0.01146 -0.0285 0.0366 1.0000
7.000 0.9192 0.02117 0.01333 -0.0275 0.0317 1.0000
7.250 0.9424 0.02253 0.01481 -0.0267 0.0280 1.0000
7.500 0.9634 0.02493 0.01733 -0.0257 0.0259 1.0000
7.750 0.9815 0.02931 0.02213 -0.0245 0.0248 1.0000
8.000 1.0012 0.03210 0.02536 -0.0233 0.0244 1.0000
8.250 1.0181 0.03537 0.02912 -0.0221 0.0241 1.0000
8.500 1.0340 0.03804 0.03227 -0.0209 0.0230 1.0000
8.750 1.0449 0.04173 0.03647 -0.0197 0.0222 1.0000
9.000 1.0476 0.04692 0.04218 -0.0185 0.0225 1.0000
9.250 1.0439 0.05246 0.04816 -0.0176 0.0230 1.0000
9.500 1.0342 0.05806 0.05410 -0.0173 0.0235 1.0000
9.750 1.0187 0.06350 0.05979 -0.0175 0.0240 1.0000
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Polar data table (+)
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