AG10 (ag10-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AG10 (ag10-il) Reynolds number: 500,000 Max Cl/Cd: 69.79 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag10-il-500000.txt Download as CSV file: xf-ag10-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG10
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6393 0.12046 0.11816 0.0356 1.0000 0.0148
-9.250 -0.6366 0.11627 0.11399 0.0327 1.0000 0.0149
-9.000 -0.6329 0.11213 0.10986 0.0304 1.0000 0.0150
-8.750 -0.6314 0.10760 0.10535 0.0298 1.0000 0.0152
-8.500 -0.6241 0.10455 0.10230 0.0301 1.0000 0.0154
-8.250 -0.6184 0.10135 0.09911 0.0291 1.0000 0.0157
-8.000 -0.6135 0.09798 0.09576 0.0276 1.0000 0.0160
-7.750 -0.6088 0.09454 0.09234 0.0257 1.0000 0.0164
-7.500 -0.6040 0.09100 0.08881 0.0232 1.0000 0.0169
-7.250 -0.5949 0.08674 0.08456 0.0188 1.0000 0.0177
-6.250 -0.5250 0.06223 0.05988 -0.0102 1.0000 0.0197
-6.000 -0.5076 0.05892 0.05653 -0.0122 1.0000 0.0200
-5.750 -0.4869 0.05533 0.05288 -0.0148 1.0000 0.0206
-5.500 -0.4632 0.05118 0.04864 -0.0181 1.0000 0.0214
-5.250 -0.4355 0.04596 0.04325 -0.0221 1.0000 0.0229
-5.000 -0.3997 0.03479 0.03146 -0.0281 1.0000 0.0251
-4.750 -0.3729 0.02396 0.01981 -0.0305 1.0000 0.0199
-4.500 -0.3452 0.01964 0.01501 -0.0310 1.0000 0.0179
-4.250 -0.3166 0.01673 0.01155 -0.0311 1.0000 0.0185
-4.000 -0.2882 0.01466 0.00906 -0.0310 1.0000 0.0189
-3.750 -0.2599 0.01286 0.00693 -0.0309 1.0000 0.0195
-3.500 -0.2323 0.01157 0.00556 -0.0308 1.0000 0.0208
-3.250 -0.2044 0.01095 0.00488 -0.0306 1.0000 0.0225
-3.000 -0.1764 0.01059 0.00444 -0.0304 1.0000 0.0245
-2.750 -0.1487 0.00975 0.00361 -0.0304 1.0000 0.0281
-2.500 -0.1208 0.00938 0.00320 -0.0302 1.0000 0.0311
-2.250 -0.0931 0.00882 0.00266 -0.0300 1.0000 0.0367
-2.000 -0.0652 0.00839 0.00223 -0.0299 1.0000 0.0431
-1.750 -0.0374 0.00811 0.00198 -0.0297 1.0000 0.0530
-1.500 -0.0098 0.00780 0.00176 -0.0296 1.0000 0.0689
-1.250 0.0177 0.00757 0.00160 -0.0294 1.0000 0.0908
-1.000 0.0449 0.00731 0.00149 -0.0292 1.0000 0.1228
-0.750 0.0720 0.00703 0.00142 -0.0291 1.0000 0.1758
-0.500 0.0988 0.00662 0.00140 -0.0290 1.0000 0.2851
-0.250 0.1163 0.00469 0.00145 -0.0270 1.0000 0.8812
0.000 0.1554 0.00453 0.00135 -0.0291 0.9866 1.0000
0.250 0.1959 0.00454 0.00129 -0.0316 0.9537 1.0000
0.500 0.2244 0.00463 0.00124 -0.0311 0.8976 1.0000
0.750 0.2469 0.00485 0.00120 -0.0293 0.8279 1.0000
1.000 0.2711 0.00518 0.00118 -0.0280 0.7492 1.0000
1.250 0.2966 0.00556 0.00119 -0.0273 0.6629 1.0000
1.500 0.3231 0.00595 0.00123 -0.0269 0.5819 1.0000
1.750 0.3502 0.00631 0.00129 -0.0267 0.5125 1.0000
2.000 0.3776 0.00663 0.00137 -0.0266 0.4573 1.0000
2.250 0.4052 0.00691 0.00147 -0.0265 0.4130 1.0000
2.500 0.4328 0.00718 0.00158 -0.0264 0.3758 1.0000
2.750 0.4605 0.00743 0.00169 -0.0263 0.3425 1.0000
3.000 0.4882 0.00767 0.00182 -0.0263 0.3114 1.0000
3.250 0.5159 0.00792 0.00197 -0.0262 0.2819 1.0000
3.500 0.5435 0.00818 0.00213 -0.0262 0.2531 1.0000
3.750 0.5710 0.00846 0.00230 -0.0261 0.2249 1.0000
4.000 0.5985 0.00876 0.00249 -0.0260 0.1971 1.0000
4.250 0.6259 0.00908 0.00272 -0.0260 0.1703 1.0000
4.500 0.6532 0.00940 0.00295 -0.0259 0.1449 1.0000
4.750 0.6805 0.00975 0.00321 -0.0258 0.1210 1.0000
5.000 0.7076 0.01014 0.00351 -0.0257 0.0981 1.0000
5.250 0.7345 0.01059 0.00387 -0.0256 0.0756 1.0000
5.500 0.7613 0.01105 0.00426 -0.0255 0.0556 1.0000
5.750 0.7880 0.01165 0.00479 -0.0253 0.0392 1.0000
6.000 0.8144 0.01230 0.00542 -0.0251 0.0287 1.0000
6.250 0.8408 0.01298 0.00613 -0.0249 0.0228 1.0000
6.500 0.8664 0.01390 0.00712 -0.0246 0.0195 1.0000
6.750 0.8925 0.01458 0.00787 -0.0242 0.0176 1.0000
7.000 0.9173 0.01561 0.00897 -0.0239 0.0160 1.0000
7.250 0.9414 0.01689 0.01039 -0.0233 0.0151 1.0000
7.500 0.9665 0.01772 0.01133 -0.0229 0.0141 1.0000
7.750 0.9913 0.01858 0.01228 -0.0225 0.0131 1.0000
8.000 1.0148 0.01976 0.01356 -0.0221 0.0126 1.0000
8.250 1.0363 0.02165 0.01559 -0.0214 0.0121 1.0000
8.500 1.0556 0.02438 0.01861 -0.0205 0.0118 1.0000
8.750 1.0770 0.02610 0.02063 -0.0198 0.0116 1.0000
9.000 1.0960 0.02846 0.02335 -0.0190 0.0114 1.0000
9.250 1.1114 0.03155 0.02686 -0.0181 0.0113 1.0000
9.500 1.1216 0.03554 0.03132 -0.0171 0.0113 1.0000
9.750 1.1252 0.04040 0.03664 -0.0162 0.0115 1.0000
10.000 1.1206 0.04602 0.04268 -0.0157 0.0117 1.0000
10.250 1.1200 0.05035 0.04719 -0.0152 0.0120 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG10 (ag10-il)