AG09 (ag09-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG09 (ag09-il) Reynolds number: 200,000 Max Cl/Cd: 56.35 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag09-il-200000.txt Download as CSV file: xf-ag09-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6223 0.13480 0.13122 0.0354 1.0000 0.0300
-10.000 -0.6211 0.13221 0.12866 0.0318 1.0000 0.0304
-9.750 -0.6181 0.12910 0.12557 0.0288 1.0000 0.0306
-9.500 -0.6143 0.12569 0.12219 0.0261 1.0000 0.0307
-9.250 -0.6096 0.12211 0.11862 0.0238 1.0000 0.0308
-9.000 -0.6049 0.11841 0.11495 0.0214 1.0000 0.0308
-8.750 -0.6038 0.11140 0.10797 0.0221 1.0000 0.0315
-8.500 -0.5946 0.10724 0.10381 0.0238 1.0000 0.0324
-8.250 -0.5879 0.10370 0.10028 0.0234 1.0000 0.0332
-8.000 -0.5822 0.10024 0.09684 0.0222 1.0000 0.0340
-7.750 -0.5770 0.09675 0.09338 0.0205 1.0000 0.0349
-7.500 -0.5719 0.09321 0.08986 0.0183 1.0000 0.0359
-7.250 -0.5650 0.08939 0.08607 0.0150 1.0000 0.0370
-7.000 -0.5543 0.08516 0.08184 0.0102 1.0000 0.0385
-6.750 -0.5361 0.08025 0.07691 0.0008 1.0000 0.0408
-6.500 -0.5058 0.07489 0.07140 -0.0121 1.0000 0.0419
-6.250 -0.4839 0.06995 0.06632 -0.0174 1.0000 0.0421
-6.000 -0.4816 0.06343 0.05991 -0.0168 1.0000 0.0435
-5.750 -0.4674 0.06030 0.05676 -0.0168 1.0000 0.0450
-5.500 -0.4478 0.05680 0.05319 -0.0188 1.0000 0.0476
-5.250 -0.4023 0.05252 0.04826 -0.0278 1.0000 0.0545
-5.000 -0.3929 0.04645 0.04241 -0.0280 1.0000 0.0568
-4.750 -0.3715 0.04349 0.03939 -0.0287 1.0000 0.0592
-4.500 -0.3424 0.03994 0.03556 -0.0309 1.0000 0.0653
-4.250 -0.3146 0.03521 0.03045 -0.0331 1.0000 0.0699
-4.000 -0.2791 0.02559 0.01985 -0.0342 1.0000 0.0401
-3.750 -0.2507 0.02131 0.01500 -0.0344 1.0000 0.0380
-3.500 -0.2221 0.01899 0.01214 -0.0342 1.0000 0.0404
-3.250 -0.1936 0.01740 0.01011 -0.0337 1.0000 0.0422
-3.000 -0.1665 0.01482 0.00728 -0.0335 1.0000 0.0454
-2.750 -0.1393 0.01406 0.00643 -0.0331 1.0000 0.0522
-2.500 -0.1124 0.01289 0.00521 -0.0327 1.0000 0.0602
-2.250 -0.0856 0.01212 0.00440 -0.0323 1.0000 0.0724
-2.000 -0.0590 0.01147 0.00379 -0.0319 1.0000 0.0877
-1.750 -0.0324 0.01104 0.00337 -0.0315 1.0000 0.1084
-1.500 -0.0062 0.01048 0.00296 -0.0312 1.0000 0.1329
-1.250 0.0201 0.01000 0.00261 -0.0309 1.0000 0.1661
-1.000 0.0462 0.00941 0.00237 -0.0307 1.0000 0.2312
-0.750 0.0691 0.00695 0.00225 -0.0293 1.0000 1.0000
-0.500 0.0950 0.00699 0.00212 -0.0289 1.0000 1.0000
-0.250 0.1208 0.00703 0.00207 -0.0284 1.0000 1.0000
0.000 0.1465 0.00709 0.00204 -0.0280 1.0000 1.0000
0.250 0.1720 0.00717 0.00208 -0.0277 1.0000 1.0000
0.500 0.1976 0.00728 0.00216 -0.0275 1.0000 1.0000
0.750 0.2456 0.00731 0.00217 -0.0318 0.9843 1.0000
1.000 0.2916 0.00731 0.00215 -0.0354 0.9585 1.0000
1.250 0.3310 0.00730 0.00212 -0.0373 0.9232 1.0000
1.500 0.3609 0.00735 0.00210 -0.0369 0.8772 1.0000
1.750 0.3847 0.00749 0.00210 -0.0351 0.8251 1.0000
2.000 0.4078 0.00771 0.00212 -0.0334 0.7696 1.0000
2.250 0.4316 0.00799 0.00217 -0.0319 0.7104 1.0000
2.500 0.4559 0.00834 0.00225 -0.0307 0.6484 1.0000
2.750 0.4808 0.00872 0.00239 -0.0299 0.5860 1.0000
3.000 0.5062 0.00914 0.00255 -0.0292 0.5251 1.0000
3.250 0.5318 0.00958 0.00274 -0.0287 0.4699 1.0000
3.500 0.5577 0.01003 0.00297 -0.0283 0.4213 1.0000
3.750 0.5838 0.01046 0.00327 -0.0279 0.3776 1.0000
4.000 0.6101 0.01090 0.00357 -0.0276 0.3384 1.0000
4.250 0.6364 0.01133 0.00390 -0.0274 0.3026 1.0000
4.500 0.6626 0.01178 0.00425 -0.0271 0.2694 1.0000
4.750 0.6888 0.01225 0.00462 -0.0269 0.2380 1.0000
5.000 0.7151 0.01269 0.00506 -0.0267 0.2062 1.0000
5.250 0.7412 0.01318 0.00548 -0.0265 0.1737 1.0000
5.500 0.7671 0.01374 0.00596 -0.0263 0.1378 1.0000
5.750 0.7923 0.01456 0.00661 -0.0260 0.0950 1.0000
6.000 0.8164 0.01588 0.00780 -0.0255 0.0583 1.0000
6.250 0.8392 0.01754 0.00938 -0.0249 0.0413 1.0000
6.500 0.8638 0.01881 0.01079 -0.0241 0.0349 1.0000
6.750 0.8850 0.02124 0.01326 -0.0232 0.0302 1.0000
7.000 0.9101 0.02230 0.01454 -0.0225 0.0270 1.0000
7.250 0.9335 0.02425 0.01671 -0.0217 0.0253 1.0000
7.500 0.9561 0.02652 0.01928 -0.0208 0.0243 1.0000
7.750 0.9773 0.02930 0.02243 -0.0199 0.0238 1.0000
8.000 0.9960 0.03295 0.02660 -0.0187 0.0240 1.0000
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Polar data table (+)
Polar graphs
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