AG10 (ag10-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG10 (ag10-il) Reynolds number: 100,000 Max Cl/Cd: 41.22 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag10-il-100000.txt Download as CSV file: xf-ag10-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6246 0.12520 0.12018 0.0306 1.0000 0.0621
-9.000 -0.6274 0.12331 0.11835 0.0258 1.0000 0.0626
-8.750 -0.6291 0.12100 0.11610 0.0208 1.0000 0.0629
-8.500 -0.6178 0.11390 0.10902 0.0233 1.0000 0.0639
-8.250 -0.6034 0.10882 0.10392 0.0263 1.0000 0.0660
-8.000 -0.5964 0.10524 0.10033 0.0257 1.0000 0.0681
-7.750 -0.5914 0.10185 0.09698 0.0240 1.0000 0.0708
-7.500 -0.5885 0.09867 0.09385 0.0204 1.0000 0.0737
-7.250 -0.5788 0.09562 0.09080 0.0059 1.0000 0.0759
-7.000 -0.5699 0.09003 0.08523 0.0031 1.0000 0.0772
-6.750 -0.5620 0.08613 0.08138 0.0099 1.0000 0.0803
-6.500 -0.5493 0.08233 0.07758 0.0076 1.0000 0.0841
-6.250 -0.5167 0.07879 0.07364 -0.0128 1.0000 0.0904
-6.000 -0.5119 0.07269 0.06779 -0.0075 1.0000 0.0921
-5.750 -0.4995 0.06911 0.06425 -0.0057 1.0000 0.0953
-5.500 -0.4646 0.06488 0.05960 -0.0181 1.0000 0.1054
-5.250 -0.4546 0.06025 0.05515 -0.0151 1.0000 0.1077
-5.000 -0.4353 0.05689 0.05176 -0.0158 1.0000 0.1142
-4.750 -0.4092 0.05251 0.04720 -0.0199 1.0000 0.1232
-4.500 -0.3830 0.04894 0.04343 -0.0229 1.0000 0.1368
-4.250 -0.3598 0.04573 0.04014 -0.0241 1.0000 0.1522
-4.000 -0.3357 0.04257 0.03686 -0.0251 1.0000 0.1677
-3.750 -0.2954 0.02255 0.01735 -0.0239 1.0000 0.1854
-3.500 -0.2519 0.02968 0.02234 -0.0317 1.0000 0.0866
-3.250 -0.2208 0.02602 0.01815 -0.0322 1.0000 0.0828
-3.000 -0.1887 0.02269 0.01407 -0.0323 1.0000 0.0794
-2.750 -0.1600 0.02077 0.01190 -0.0320 1.0000 0.0833
-2.500 -0.1305 0.01924 0.00992 -0.0316 1.0000 0.0895
-2.250 -0.1029 0.01761 0.00823 -0.0313 1.0000 0.0987
-2.000 -0.0752 0.01627 0.00683 -0.0308 1.0000 0.1107
-1.750 -0.0480 0.01524 0.00582 -0.0303 1.0000 0.1304
-1.500 -0.0214 0.01419 0.00494 -0.0299 1.0000 0.1592
-1.250 0.0048 0.01320 0.00419 -0.0293 1.0000 0.2081
-1.000 0.0294 0.01124 0.00356 -0.0289 1.0000 0.4582
-0.750 0.0546 0.00978 0.00309 -0.0268 1.0000 1.0000
-0.500 0.0811 0.00979 0.00289 -0.0263 1.0000 1.0000
-0.250 0.1073 0.00982 0.00276 -0.0259 1.0000 1.0000
0.000 0.1333 0.00985 0.00269 -0.0255 1.0000 1.0000
0.250 0.1592 0.00990 0.00268 -0.0250 1.0000 1.0000
0.500 0.1848 0.00997 0.00270 -0.0246 1.0000 1.0000
0.750 0.2103 0.01005 0.00278 -0.0242 1.0000 1.0000
1.000 0.2356 0.01016 0.00290 -0.0238 1.0000 1.0000
1.250 0.2607 0.01029 0.00307 -0.0234 1.0000 1.0000
1.500 0.2857 0.01045 0.00331 -0.0232 1.0000 1.0000
1.750 0.3103 0.01067 0.00363 -0.0231 1.0000 1.0000
2.000 0.3688 0.01075 0.00387 -0.0295 0.9667 1.0000
2.250 0.4252 0.01070 0.00391 -0.0339 0.8818 1.0000
2.500 0.4514 0.01095 0.00389 -0.0315 0.7681 1.0000
2.750 0.4717 0.01152 0.00399 -0.0284 0.6594 1.0000
3.000 0.4944 0.01221 0.00422 -0.0266 0.5725 1.0000
3.250 0.5186 0.01291 0.00455 -0.0255 0.5062 1.0000
3.500 0.5436 0.01359 0.00498 -0.0247 0.4522 1.0000
3.750 0.5689 0.01428 0.00542 -0.0240 0.4055 1.0000
4.000 0.5946 0.01494 0.00591 -0.0235 0.3621 1.0000
4.250 0.6204 0.01560 0.00645 -0.0230 0.3215 1.0000
4.500 0.6460 0.01632 0.00704 -0.0225 0.2841 1.0000
4.750 0.6718 0.01702 0.00767 -0.0221 0.2466 1.0000
5.000 0.6972 0.01784 0.00833 -0.0217 0.2120 1.0000
5.250 0.7228 0.01869 0.00920 -0.0213 0.1763 1.0000
5.500 0.7478 0.01974 0.01012 -0.0208 0.1440 1.0000
5.750 0.7726 0.02104 0.01132 -0.0203 0.1158 1.0000
6.000 0.7978 0.02258 0.01296 -0.0197 0.0938 1.0000
6.250 0.8228 0.02435 0.01481 -0.0191 0.0793 1.0000
6.500 0.8477 0.02644 0.01709 -0.0184 0.0692 1.0000
6.750 0.8713 0.02929 0.01995 -0.0179 0.0630 1.0000
7.000 0.8955 0.03154 0.02287 -0.0171 0.0577 1.0000
7.250 0.9177 0.03464 0.02638 -0.0164 0.0552 1.0000
7.500 0.9376 0.03851 0.03076 -0.0157 0.0542 1.0000
7.750 0.9544 0.04279 0.03551 -0.0152 0.0534 1.0000
8.000 0.9665 0.04811 0.04121 -0.0150 0.0523 1.0000
8.250 0.9751 0.05373 0.04733 -0.0150 0.0522 1.0000
8.500 0.9519 0.06657 0.06147 -0.0187 0.0604 1.0000
8.750 0.9515 0.07250 0.06753 -0.0200 0.0620 1.0000
9.000 0.8917 0.10386 0.09922 -0.0464 0.1292 1.0000
9.250 0.8994 0.10943 0.10478 -0.0448 0.1276 1.0000
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Polar data table (+)
Polar graphs
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