AG09 (ag09-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG09 (ag09-il) Reynolds number: 1,000,000 Max Cl/Cd: 87 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag09-il-1000000.txt Download as CSV file: xf-ag09-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG09
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 -0.6011 0.09874 0.09720 0.0249 1.0000 0.0099
-8.000 -0.5971 0.09477 0.09323 0.0226 1.0000 0.0099
-7.750 -0.5931 0.09071 0.08920 0.0198 1.0000 0.0100
-5.500 -0.4340 0.01803 0.01450 -0.0340 1.0000 0.0090
-5.250 -0.4074 0.01562 0.01169 -0.0340 1.0000 0.0095
-5.000 -0.3802 0.01448 0.01032 -0.0339 1.0000 0.0098
-4.750 -0.3531 0.01307 0.00865 -0.0338 1.0000 0.0101
-4.500 -0.3262 0.01076 0.00596 -0.0338 1.0000 0.0105
-4.250 -0.2989 0.00975 0.00481 -0.0336 1.0000 0.0112
-4.000 -0.2714 0.00931 0.00433 -0.0335 1.0000 0.0121
-3.750 -0.2437 0.00877 0.00373 -0.0333 1.0000 0.0130
-3.500 -0.2161 0.00835 0.00326 -0.0331 1.0000 0.0142
-3.250 -0.1885 0.00788 0.00271 -0.0329 1.0000 0.0153
-3.000 -0.1608 0.00737 0.00216 -0.0328 1.0000 0.0185
-2.750 -0.1334 0.00717 0.00195 -0.0326 1.0000 0.0211
-2.500 -0.1060 0.00684 0.00164 -0.0323 1.0000 0.0280
-2.250 -0.0787 0.00662 0.00143 -0.0321 1.0000 0.0363
-2.000 -0.0518 0.00645 0.00129 -0.0318 1.0000 0.0462
-1.750 -0.0212 0.00628 0.00118 -0.0324 0.9967 0.0596
-1.500 0.0155 0.00610 0.00108 -0.0343 0.9843 0.0756
-1.250 0.0496 0.00597 0.00098 -0.0355 0.9618 0.0937
-1.000 0.0766 0.00588 0.00091 -0.0350 0.9267 0.1154
-0.500 0.1262 0.00582 0.00080 -0.0331 0.8423 0.1854
-0.250 0.1525 0.00575 0.00075 -0.0327 0.7993 0.2524
0.000 0.1791 0.00535 0.00074 -0.0326 0.7565 0.4422
0.250 0.2000 0.00418 0.00077 -0.0312 0.7142 0.8814
0.500 0.2285 0.00415 0.00072 -0.0310 0.6677 1.0000
0.750 0.2560 0.00435 0.00072 -0.0308 0.6205 1.0000
1.000 0.2835 0.00456 0.00073 -0.0307 0.5734 1.0000
1.250 0.3111 0.00477 0.00075 -0.0306 0.5275 1.0000
1.500 0.3388 0.00499 0.00079 -0.0305 0.4827 1.0000
1.750 0.3664 0.00521 0.00085 -0.0304 0.4417 1.0000
2.000 0.3941 0.00542 0.00091 -0.0304 0.4050 1.0000
2.250 0.4218 0.00563 0.00098 -0.0303 0.3700 1.0000
2.500 0.4495 0.00583 0.00106 -0.0302 0.3395 1.0000
2.750 0.4772 0.00605 0.00117 -0.0302 0.3092 1.0000
3.000 0.5049 0.00626 0.00127 -0.0301 0.2819 1.0000
3.250 0.5325 0.00647 0.00138 -0.0301 0.2561 1.0000
3.500 0.5601 0.00669 0.00151 -0.0300 0.2308 1.0000
3.750 0.5876 0.00692 0.00167 -0.0300 0.2073 1.0000
4.250 0.6424 0.00742 0.00199 -0.0298 0.1605 1.0000
4.500 0.6697 0.00770 0.00218 -0.0298 0.1373 1.0000
4.750 0.6969 0.00801 0.00241 -0.0297 0.1129 1.0000
5.000 0.7238 0.00837 0.00266 -0.0296 0.0879 1.0000
5.250 0.7506 0.00878 0.00295 -0.0295 0.0630 1.0000
5.500 0.7772 0.00924 0.00328 -0.0294 0.0410 1.0000
5.750 0.8038 0.00968 0.00366 -0.0292 0.0260 1.0000
6.000 0.8301 0.01031 0.00425 -0.0290 0.0144 1.0000
6.250 0.8568 0.01070 0.00468 -0.0288 0.0118 1.0000
6.500 0.8827 0.01147 0.00555 -0.0284 0.0093 1.0000
6.750 0.9090 0.01197 0.00613 -0.0281 0.0085 1.0000
7.000 0.9349 0.01255 0.00679 -0.0278 0.0078 1.0000
7.250 0.9607 0.01313 0.00742 -0.0275 0.0072 1.0000
7.500 0.9854 0.01398 0.00837 -0.0271 0.0067 1.0000
7.750 1.0085 0.01534 0.00990 -0.0265 0.0064 1.0000
8.000 1.0288 0.01743 0.01223 -0.0256 0.0061 1.0000
8.250 1.0525 0.01843 0.01336 -0.0251 0.0060 1.0000
8.500 1.0759 0.01943 0.01450 -0.0246 0.0059 1.0000
8.750 1.0986 0.02058 0.01582 -0.0240 0.0058 1.0000
9.000 1.1203 0.02195 0.01737 -0.0233 0.0055 1.0000
9.250 1.1406 0.02360 0.01922 -0.0226 0.0053 1.0000
9.500 1.1590 0.02557 0.02144 -0.0217 0.0051 1.0000
9.750 1.1743 0.02811 0.02427 -0.0207 0.0049 1.0000
10.000 1.1842 0.03161 0.02815 -0.0195 0.0049 1.0000
10.250 1.1830 0.03686 0.03391 -0.0180 0.0049 1.0000
10.500 1.1685 0.04340 0.04094 -0.0170 0.0051 1.0000
10.750 1.1478 0.04899 0.04685 -0.0165 0.0052 1.0000
11.000 1.1281 0.05455 0.05260 -0.0197 0.0053 1.0000
11.250 1.1123 0.06371 0.06196 -0.0299 0.0053 1.0000
11.500 1.0961 0.07528 0.07367 -0.0407 0.0053 1.0000
11.750 1.0749 0.08668 0.08515 -0.0484 0.0053 1.0000
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