AG09 (ag09-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG09 (ag09-il) Reynolds number: 500,000 Max Cl/Cd: 70.68 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag09-il-500000-n5.txt Download as CSV file: xf-ag09-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6018 0.09842 0.09622 0.0251 1.0000 0.0092
-8.000 -0.5986 0.09441 0.09223 0.0228 1.0000 0.0092
-7.750 -0.5952 0.09052 0.08836 0.0204 1.0000 0.0089
-7.500 -0.5900 0.08614 0.08400 0.0166 1.0000 0.0085
-7.250 -0.5805 0.08088 0.07875 0.0110 1.0000 0.0081
-7.000 -0.5682 0.07467 0.07252 0.0040 1.0000 0.0077
-6.750 -0.5525 0.06622 0.06401 -0.0054 1.0000 0.0073
-6.500 -0.5323 0.05651 0.05418 -0.0151 1.0000 0.0070
-6.250 -0.5086 0.04773 0.04520 -0.0226 1.0000 0.0071
-6.000 -0.4861 0.02075 0.01659 -0.0339 1.0000 0.0075
-5.750 -0.4604 0.01818 0.01357 -0.0341 1.0000 0.0079
-5.500 -0.4340 0.01629 0.01132 -0.0342 1.0000 0.0082
-5.250 -0.4072 0.01495 0.00969 -0.0341 1.0000 0.0087
-5.000 -0.3801 0.01403 0.00857 -0.0340 1.0000 0.0094
-4.750 -0.3530 0.01313 0.00747 -0.0339 1.0000 0.0098
-4.500 -0.3259 0.01192 0.00605 -0.0337 1.0000 0.0103
-4.250 -0.2988 0.01105 0.00505 -0.0335 1.0000 0.0110
-4.000 -0.2715 0.01053 0.00447 -0.0334 1.0000 0.0120
-3.750 -0.2441 0.01007 0.00394 -0.0332 1.0000 0.0131
-3.500 -0.2168 0.00965 0.00346 -0.0330 1.0000 0.0143
-3.250 -0.1895 0.00920 0.00296 -0.0328 1.0000 0.0166
-3.000 -0.1622 0.00891 0.00267 -0.0326 1.0000 0.0196
-2.750 -0.1350 0.00861 0.00234 -0.0324 1.0000 0.0226
-2.500 -0.1079 0.00833 0.00209 -0.0321 1.0000 0.0286
-2.250 -0.0807 0.00810 0.00187 -0.0319 0.9997 0.0364
-2.000 -0.0451 0.00789 0.00168 -0.0336 0.9829 0.0465
-1.750 -0.0103 0.00770 0.00153 -0.0350 0.9596 0.0597
-1.500 0.0216 0.00756 0.00140 -0.0357 0.9267 0.0737
-1.250 0.0475 0.00750 0.00128 -0.0348 0.8849 0.0882
-1.000 0.0723 0.00750 0.00118 -0.0338 0.8413 0.1053
-0.750 0.0979 0.00752 0.00110 -0.0331 0.7977 0.1249
-0.250 0.1507 0.00753 0.00098 -0.0322 0.7095 0.1944
0.000 0.1776 0.00748 0.00095 -0.0320 0.6661 0.2576
0.250 0.2044 0.00717 0.00094 -0.0320 0.6222 0.4200
0.500 0.2268 0.00573 0.00094 -0.0306 0.5808 1.0000
0.750 0.2541 0.00594 0.00093 -0.0304 0.5376 1.0000
1.000 0.2815 0.00616 0.00095 -0.0303 0.4956 1.0000
1.250 0.3089 0.00638 0.00098 -0.0301 0.4561 1.0000
1.500 0.3364 0.00660 0.00103 -0.0300 0.4203 1.0000
1.750 0.3640 0.00680 0.00110 -0.0299 0.3882 1.0000
2.000 0.3915 0.00701 0.00117 -0.0298 0.3577 1.0000
2.250 0.4190 0.00721 0.00126 -0.0298 0.3299 1.0000
2.500 0.4466 0.00742 0.00136 -0.0297 0.3039 1.0000
2.750 0.4741 0.00764 0.00148 -0.0296 0.2792 1.0000
3.000 0.5016 0.00785 0.00161 -0.0295 0.2558 1.0000
3.250 0.5290 0.00808 0.00175 -0.0294 0.2332 1.0000
3.500 0.5564 0.00833 0.00191 -0.0293 0.2111 1.0000
3.750 0.5837 0.00856 0.00211 -0.0292 0.1900 1.0000
4.000 0.6110 0.00884 0.00230 -0.0291 0.1687 1.0000
4.250 0.6381 0.00912 0.00251 -0.0290 0.1473 1.0000
4.500 0.6652 0.00943 0.00275 -0.0289 0.1261 1.0000
4.750 0.6920 0.00979 0.00304 -0.0288 0.1029 1.0000
5.000 0.7188 0.01018 0.00334 -0.0287 0.0799 1.0000
5.250 0.7453 0.01061 0.00368 -0.0286 0.0580 1.0000
5.500 0.7717 0.01110 0.00408 -0.0284 0.0392 1.0000
5.750 0.7981 0.01156 0.00451 -0.0283 0.0270 1.0000
6.000 0.8243 0.01205 0.00500 -0.0281 0.0184 1.0000
6.250 0.8505 0.01257 0.00553 -0.0278 0.0133 1.0000
6.500 0.8766 0.01309 0.00609 -0.0276 0.0107 1.0000
6.750 0.9023 0.01374 0.00682 -0.0273 0.0091 1.0000
7.000 0.9281 0.01432 0.00750 -0.0270 0.0082 1.0000
7.250 0.9535 0.01497 0.00828 -0.0266 0.0075 1.0000
7.500 0.9784 0.01572 0.00912 -0.0263 0.0069 1.0000
7.750 1.0020 0.01680 0.01032 -0.0258 0.0064 1.0000
8.000 1.0248 0.01808 0.01177 -0.0252 0.0061 1.0000
8.250 1.0486 0.01897 0.01280 -0.0248 0.0058 1.0000
8.500 1.0720 0.01990 0.01390 -0.0243 0.0055 1.0000
8.750 1.0948 0.02093 0.01509 -0.0238 0.0052 1.0000
9.000 1.1164 0.02221 0.01655 -0.0232 0.0050 1.0000
9.250 1.1372 0.02362 0.01815 -0.0226 0.0048 1.0000
9.500 1.1572 0.02510 0.01984 -0.0219 0.0046 1.0000
9.750 1.1762 0.02669 0.02164 -0.0212 0.0045 1.0000
10.000 1.1940 0.02838 0.02354 -0.0205 0.0043 1.0000
10.250 1.2101 0.03022 0.02560 -0.0198 0.0042 1.0000
10.500 1.2238 0.03235 0.02800 -0.0190 0.0041 1.0000
10.750 1.2328 0.03506 0.03099 -0.0181 0.0040 1.0000
11.000 1.2344 0.03862 0.03488 -0.0171 0.0039 1.0000
11.250 1.2264 0.04301 0.03963 -0.0163 0.0038 1.0000
11.500 1.2092 0.04744 0.04434 -0.0160 0.0038 1.0000
11.750 1.1943 0.05319 0.05032 -0.0201 0.0038 1.0000
12.000 1.1817 0.06146 0.05879 -0.0284 0.0038 1.0000
12.250 1.1687 0.07088 0.06839 -0.0366 0.0038 1.0000
12.500 1.1511 0.08057 0.07820 -0.0432 0.0039 1.0000
12.750 1.1253 0.09154 0.08929 -0.0496 0.0040 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG09 (ag09-il)