AG08 (ag08-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG08 (ag08-il) Reynolds number: 100,000 Max Cl/Cd: 45.12 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag08-il-100000-n5.txt Download as CSV file: xf-ag08-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5679 0.10455 0.09969 0.0147 1.0000 0.0406
-8.250 -0.5703 0.09979 0.09499 0.0064 1.0000 0.0363
-8.000 -0.5669 0.09296 0.08816 0.0061 1.0000 0.0253
-7.750 -0.5630 0.08904 0.08428 0.0045 1.0000 0.0247
-7.500 -0.5569 0.08462 0.07989 0.0012 1.0000 0.0242
-7.250 -0.5488 0.07978 0.07506 -0.0031 1.0000 0.0238
-7.000 -0.5385 0.07448 0.06977 -0.0082 1.0000 0.0233
-6.750 -0.5256 0.06873 0.06398 -0.0139 1.0000 0.0229
-6.500 -0.5100 0.06247 0.05764 -0.0199 1.0000 0.0226
-6.250 -0.4914 0.05565 0.05066 -0.0258 1.0000 0.0228
-6.000 -0.4705 0.04835 0.04307 -0.0311 1.0000 0.0237
-5.750 -0.4483 0.04114 0.03536 -0.0351 1.0000 0.0246
-5.500 -0.4252 0.03518 0.02874 -0.0373 1.0000 0.0251
-5.250 -0.4009 0.03044 0.02329 -0.0383 1.0000 0.0255
-5.000 -0.3759 0.02659 0.01878 -0.0387 1.0000 0.0263
-4.750 -0.3510 0.02400 0.01581 -0.0388 1.0000 0.0280
-4.500 -0.3253 0.02269 0.01425 -0.0386 1.0000 0.0321
-4.250 -0.2985 0.02076 0.01187 -0.0381 1.0000 0.0354
-4.000 -0.2724 0.01892 0.00979 -0.0377 1.0000 0.0383
-3.750 -0.2465 0.01803 0.00881 -0.0373 1.0000 0.0453
-3.500 -0.2206 0.01682 0.00746 -0.0368 1.0000 0.0516
-3.250 -0.1947 0.01604 0.00658 -0.0363 1.0000 0.0622
-3.000 -0.1689 0.01525 0.00577 -0.0358 1.0000 0.0751
-2.750 -0.1433 0.01457 0.00517 -0.0355 1.0000 0.0946
-2.500 -0.1176 0.01397 0.00462 -0.0351 1.0000 0.1189
-2.250 -0.0921 0.01343 0.00418 -0.0347 1.0000 0.1564
-2.000 -0.0666 0.01289 0.00387 -0.0343 1.0000 0.2099
-1.750 -0.0414 0.01237 0.00364 -0.0340 1.0000 0.2884
-1.500 -0.0162 0.01183 0.00348 -0.0336 1.0000 0.3981
-1.250 0.0076 0.01102 0.00332 -0.0328 1.0000 0.5759
-1.000 0.0355 0.01001 0.00318 -0.0316 1.0000 1.0000
-0.750 0.0606 0.01006 0.00307 -0.0311 1.0000 1.0000
-0.500 0.0854 0.01012 0.00301 -0.0307 1.0000 1.0000
-0.250 0.1102 0.01021 0.00299 -0.0302 1.0000 1.0000
0.000 0.1465 0.01029 0.00297 -0.0322 0.9901 1.0000
0.250 0.1901 0.01036 0.00296 -0.0354 0.9716 1.0000
0.500 0.2304 0.01041 0.00296 -0.0379 0.9486 1.0000
0.750 0.2690 0.01045 0.00295 -0.0398 0.9216 1.0000
1.000 0.3049 0.01049 0.00294 -0.0410 0.8892 1.0000
1.250 0.3371 0.01055 0.00293 -0.0413 0.8512 1.0000
1.500 0.3658 0.01065 0.00295 -0.0408 0.8087 1.0000
1.750 0.3922 0.01081 0.00297 -0.0397 0.7631 1.0000
2.000 0.4176 0.01102 0.00303 -0.0386 0.7155 1.0000
2.250 0.4428 0.01128 0.00311 -0.0375 0.6666 1.0000
2.500 0.4681 0.01159 0.00324 -0.0365 0.6179 1.0000
2.750 0.4934 0.01193 0.00344 -0.0357 0.5700 1.0000
3.000 0.5186 0.01231 0.00364 -0.0349 0.5239 1.0000
3.250 0.5439 0.01270 0.00388 -0.0342 0.4803 1.0000
3.500 0.5693 0.01312 0.00416 -0.0336 0.4395 1.0000
3.750 0.5948 0.01354 0.00452 -0.0331 0.4010 1.0000
4.000 0.6203 0.01399 0.00487 -0.0326 0.3650 1.0000
4.250 0.6458 0.01446 0.00526 -0.0321 0.3306 1.0000
4.500 0.6712 0.01494 0.00569 -0.0317 0.2976 1.0000
4.750 0.6967 0.01544 0.00615 -0.0313 0.2647 1.0000
5.000 0.7219 0.01600 0.00670 -0.0309 0.2328 1.0000
5.250 0.7470 0.01659 0.00726 -0.0305 0.2010 1.0000
5.500 0.7719 0.01723 0.00788 -0.0301 0.1684 1.0000
5.750 0.7964 0.01800 0.00857 -0.0298 0.1360 1.0000
6.000 0.8206 0.01886 0.00944 -0.0293 0.1048 1.0000
6.250 0.8442 0.01991 0.01043 -0.0289 0.0783 1.0000
6.500 0.8668 0.02118 0.01165 -0.0283 0.0586 1.0000
6.750 0.8892 0.02251 0.01303 -0.0276 0.0449 1.0000
7.000 0.9113 0.02393 0.01463 -0.0268 0.0373 1.0000
7.250 0.9324 0.02553 0.01639 -0.0260 0.0314 1.0000
7.500 0.9536 0.02712 0.01816 -0.0251 0.0275 1.0000
7.750 0.9722 0.02939 0.02061 -0.0241 0.0252 1.0000
8.000 0.9920 0.03177 0.02330 -0.0230 0.0236 1.0000
8.250 1.0115 0.03392 0.02585 -0.0221 0.0212 1.0000
8.500 1.0291 0.03616 0.02842 -0.0212 0.0193 1.0000
8.750 1.0440 0.03900 0.03161 -0.0203 0.0184 1.0000
9.000 1.0558 0.04220 0.03518 -0.0193 0.0177 1.0000
9.250 1.0632 0.04596 0.03931 -0.0184 0.0173 1.0000
9.500 1.0650 0.05029 0.04406 -0.0175 0.0170 1.0000
9.750 1.0608 0.05495 0.04912 -0.0168 0.0168 1.0000
10.000 1.0513 0.05962 0.05415 -0.0166 0.0168 1.0000
10.250 1.0363 0.06401 0.05880 -0.0167 0.0168 1.0000
10.500 1.0195 0.06926 0.06429 -0.0195 0.0169 1.0000
10.750 1.0010 0.07671 0.07197 -0.0261 0.0171 1.0000
11.000 0.9652 0.09255 0.08806 -0.0403 0.0180 1.0000
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Polar data table (+)
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