AG08 (ag08-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG08 (ag08-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.04 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag08-il-1000000.txt Download as CSV file: xf-ag08-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4788 0.08037 0.07892 0.0051 1.0000 0.0091
-8.000 -0.4803 0.07590 0.07446 0.0036 1.0000 0.0092
-7.750 -0.4826 0.07137 0.06995 0.0019 1.0000 0.0094
-7.500 -0.4862 0.06671 0.06530 -0.0002 1.0000 0.0095
-7.250 -0.6016 0.02396 0.02113 -0.0391 1.0000 0.0052
-7.000 -0.5786 0.02123 0.01808 -0.0395 1.0000 0.0055
-6.750 -0.5540 0.01955 0.01616 -0.0397 1.0000 0.0058
-6.500 -0.5290 0.01781 0.01415 -0.0397 1.0000 0.0063
-6.250 -0.5037 0.01606 0.01211 -0.0396 1.0000 0.0067
-6.000 -0.4778 0.01467 0.01046 -0.0394 1.0000 0.0071
-5.750 -0.4515 0.01371 0.00932 -0.0392 1.0000 0.0073
-5.500 -0.4252 0.01257 0.00797 -0.0389 1.0000 0.0076
-5.250 -0.3997 0.01062 0.00574 -0.0386 1.0000 0.0085
-5.000 -0.3729 0.01035 0.00546 -0.0384 1.0000 0.0095
-4.750 -0.3461 0.00997 0.00504 -0.0381 1.0000 0.0106
-4.500 -0.3194 0.00961 0.00460 -0.0377 1.0000 0.0114
-4.250 -0.2931 0.00861 0.00346 -0.0373 1.0000 0.0129
-4.000 -0.2667 0.00823 0.00305 -0.0369 1.0000 0.0148
-3.750 -0.2406 0.00804 0.00286 -0.0365 1.0000 0.0169
-3.500 -0.2144 0.00757 0.00231 -0.0360 1.0000 0.0202
-3.250 -0.1883 0.00732 0.00207 -0.0355 1.0000 0.0246
-3.000 -0.1623 0.00705 0.00180 -0.0350 1.0000 0.0319
-2.750 -0.1349 0.00684 0.00162 -0.0349 0.9995 0.0422
-2.500 -0.0984 0.00660 0.00145 -0.0368 0.9960 0.0579
-2.250 -0.0625 0.00639 0.00130 -0.0385 0.9918 0.0767
-2.000 -0.0272 0.00617 0.00117 -0.0401 0.9846 0.1017
-1.750 0.0065 0.00593 0.00106 -0.0414 0.9736 0.1388
-1.500 0.0381 0.00571 0.00096 -0.0421 0.9575 0.1830
-1.250 0.0653 0.00551 0.00089 -0.0418 0.9335 0.2349
-1.000 0.0905 0.00535 0.00083 -0.0410 0.9037 0.2961
-0.750 0.1157 0.00521 0.00078 -0.0402 0.8707 0.3652
-0.500 0.1415 0.00505 0.00075 -0.0397 0.8343 0.4529
-0.250 0.1672 0.00478 0.00073 -0.0392 0.7952 0.5845
0.000 0.1891 0.00410 0.00074 -0.0378 0.7571 0.8474
0.250 0.2188 0.00397 0.00071 -0.0377 0.7157 1.0000
0.500 0.2459 0.00415 0.00071 -0.0374 0.6747 1.0000
0.750 0.2731 0.00434 0.00071 -0.0372 0.6315 1.0000
1.000 0.3004 0.00454 0.00073 -0.0370 0.5884 1.0000
1.250 0.3278 0.00474 0.00076 -0.0369 0.5470 1.0000
1.500 0.3552 0.00496 0.00081 -0.0367 0.5049 1.0000
1.750 0.3826 0.00517 0.00087 -0.0366 0.4658 1.0000
2.000 0.4101 0.00537 0.00093 -0.0365 0.4304 1.0000
2.250 0.4376 0.00558 0.00101 -0.0364 0.3964 1.0000
2.500 0.4651 0.00579 0.00109 -0.0363 0.3650 1.0000
2.750 0.4927 0.00599 0.00120 -0.0362 0.3362 1.0000
3.000 0.5201 0.00620 0.00130 -0.0361 0.3077 1.0000
3.250 0.5476 0.00642 0.00142 -0.0361 0.2809 1.0000
3.500 0.5750 0.00664 0.00154 -0.0360 0.2559 1.0000
3.750 0.6023 0.00688 0.00170 -0.0359 0.2301 1.0000
4.000 0.6296 0.00713 0.00186 -0.0358 0.2053 1.0000
4.250 0.6567 0.00739 0.00203 -0.0357 0.1801 1.0000
4.500 0.6838 0.00768 0.00222 -0.0356 0.1546 1.0000
4.750 0.7106 0.00801 0.00245 -0.0354 0.1279 1.0000
5.000 0.7374 0.00837 0.00270 -0.0353 0.1024 1.0000
5.250 0.7640 0.00873 0.00297 -0.0352 0.0804 1.0000
5.500 0.7905 0.00915 0.00328 -0.0350 0.0591 1.0000
5.750 0.8170 0.00954 0.00360 -0.0348 0.0423 1.0000
6.000 0.8431 0.01002 0.00401 -0.0346 0.0274 1.0000
6.250 0.8691 0.01059 0.00455 -0.0343 0.0165 1.0000
6.500 0.8954 0.01101 0.00499 -0.0340 0.0133 1.0000
6.750 0.9210 0.01169 0.00576 -0.0336 0.0104 1.0000
7.000 0.9471 0.01210 0.00621 -0.0333 0.0091 1.0000
7.250 0.9727 0.01265 0.00682 -0.0330 0.0081 1.0000
7.500 0.9969 0.01360 0.00790 -0.0324 0.0072 1.0000
7.750 1.0195 0.01488 0.00936 -0.0317 0.0067 1.0000
8.000 1.0443 0.01551 0.01008 -0.0312 0.0065 1.0000
8.250 1.0684 0.01629 0.01096 -0.0307 0.0061 1.0000
8.500 1.0919 0.01718 0.01197 -0.0301 0.0057 1.0000
8.750 1.1147 0.01819 0.01309 -0.0295 0.0053 1.0000
9.000 1.1366 0.01932 0.01438 -0.0288 0.0051 1.0000
9.250 1.1575 0.02063 0.01584 -0.0280 0.0049 1.0000
9.500 1.1777 0.02199 0.01734 -0.0272 0.0047 1.0000
9.750 1.1949 0.02387 0.01941 -0.0262 0.0044 1.0000
10.000 1.2038 0.02739 0.02329 -0.0245 0.0042 1.0000
10.250 1.2085 0.03136 0.02766 -0.0227 0.0042 1.0000
10.500 1.2103 0.03526 0.03193 -0.0210 0.0041 1.0000
10.750 1.2078 0.03919 0.03618 -0.0194 0.0041 1.0000
11.000 1.1992 0.04311 0.04038 -0.0178 0.0041 1.0000
11.250 1.1841 0.04669 0.04417 -0.0164 0.0041 1.0000
11.500 1.1702 0.05122 0.04888 -0.0182 0.0041 1.0000
11.750 1.1588 0.05724 0.05507 -0.0233 0.0041 1.0000
12.000 1.1463 0.06539 0.06339 -0.0310 0.0041 1.0000
12.250 1.1374 0.07326 0.07138 -0.0376 0.0042 1.0000
12.500 1.1255 0.08162 0.07983 -0.0436 0.0042 1.0000
12.750 1.1100 0.09043 0.08872 -0.0490 0.0042 1.0000
13.000 1.0963 0.09852 0.09688 -0.0534 0.0042 1.0000
13.250 1.0807 0.10707 0.10549 -0.0578 0.0043 1.0000
13.500 1.0611 0.11666 0.11514 -0.0623 0.0044 1.0000
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Polar data table (+)
Polar graphs
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