AG09 (ag09-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG09 (ag09-il) Reynolds number: 1,000,000 Max Cl/Cd: 82 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag09-il-1000000-n5.txt Download as CSV file: xf-ag09-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6317 0.10022 0.09866 0.0283 1.0000 0.0043
-8.500 -0.6291 0.09620 0.09466 0.0262 1.0000 0.0044
-7.750 -0.6696 0.02355 0.02068 -0.0333 1.0000 0.0045
-7.500 -0.6470 0.01972 0.01639 -0.0340 1.0000 0.0047
-7.250 -0.6221 0.01779 0.01419 -0.0343 1.0000 0.0048
-7.000 -0.5962 0.01660 0.01279 -0.0343 1.0000 0.0050
-6.750 -0.5701 0.01544 0.01144 -0.0343 1.0000 0.0053
-6.500 -0.5437 0.01432 0.01012 -0.0343 1.0000 0.0055
-6.250 -0.5170 0.01333 0.00894 -0.0343 1.0000 0.0057
-6.000 -0.4901 0.01249 0.00793 -0.0342 1.0000 0.0060
-5.750 -0.4630 0.01173 0.00702 -0.0341 1.0000 0.0062
-5.500 -0.4357 0.01108 0.00624 -0.0340 1.0000 0.0064
-5.250 -0.4084 0.01054 0.00559 -0.0339 1.0000 0.0065
-5.000 -0.3810 0.01002 0.00499 -0.0337 1.0000 0.0066
-4.750 -0.3536 0.00927 0.00412 -0.0336 1.0000 0.0073
-4.500 -0.3260 0.00891 0.00373 -0.0335 1.0000 0.0079
-4.250 -0.2984 0.00859 0.00336 -0.0334 1.0000 0.0085
-4.000 -0.2708 0.00826 0.00299 -0.0333 1.0000 0.0092
-3.750 -0.2431 0.00799 0.00268 -0.0331 1.0000 0.0098
-3.500 -0.2155 0.00766 0.00232 -0.0330 1.0000 0.0108
-3.250 -0.1860 0.00740 0.00205 -0.0333 0.9950 0.0125
-3.000 -0.1520 0.00719 0.00182 -0.0345 0.9737 0.0144
-2.750 -0.1214 0.00701 0.00161 -0.0349 0.9414 0.0178
-2.500 -0.0966 0.00696 0.00146 -0.0339 0.9006 0.0214
-2.250 -0.0715 0.00692 0.00130 -0.0331 0.8576 0.0276
-2.000 -0.0453 0.00694 0.00117 -0.0325 0.8144 0.0339
-1.750 -0.0183 0.00694 0.00106 -0.0321 0.7739 0.0421
-1.500 0.0090 0.00695 0.00096 -0.0319 0.7337 0.0524
-1.250 0.0365 0.00697 0.00087 -0.0318 0.6929 0.0641
-1.000 0.0641 0.00701 0.00080 -0.0316 0.6519 0.0766
-0.750 0.0918 0.00706 0.00075 -0.0316 0.6110 0.0901
-0.500 0.1196 0.00710 0.00071 -0.0315 0.5719 0.1075
-0.250 0.1474 0.00716 0.00068 -0.0315 0.5332 0.1253
0.000 0.1753 0.00719 0.00066 -0.0315 0.4957 0.1519
0.250 0.2031 0.00721 0.00067 -0.0315 0.4594 0.1895
0.500 0.2310 0.00720 0.00068 -0.0315 0.4262 0.2414
0.750 0.2588 0.00708 0.00071 -0.0317 0.3957 0.3351
1.000 0.2826 0.00576 0.00079 -0.0314 0.3693 0.8432
1.250 0.3087 0.00557 0.00080 -0.0306 0.3447 1.0000
1.500 0.3366 0.00573 0.00084 -0.0305 0.3199 1.0000
1.750 0.3645 0.00589 0.00090 -0.0305 0.2967 1.0000
2.000 0.3924 0.00604 0.00096 -0.0304 0.2756 1.0000
2.250 0.4202 0.00621 0.00103 -0.0304 0.2539 1.0000
2.500 0.4480 0.00637 0.00111 -0.0303 0.2354 1.0000
2.750 0.4757 0.00655 0.00122 -0.0303 0.2146 1.0000
3.000 0.5034 0.00674 0.00132 -0.0302 0.1964 1.0000
3.250 0.5311 0.00692 0.00144 -0.0302 0.1785 1.0000
3.500 0.5587 0.00714 0.00157 -0.0301 0.1590 1.0000
3.750 0.5863 0.00735 0.00173 -0.0301 0.1412 1.0000
4.000 0.6138 0.00758 0.00189 -0.0300 0.1230 1.0000
4.250 0.6411 0.00786 0.00208 -0.0299 0.1024 1.0000
4.500 0.6683 0.00815 0.00228 -0.0298 0.0824 1.0000
4.750 0.6954 0.00849 0.00254 -0.0297 0.0621 1.0000
5.000 0.7223 0.00886 0.00281 -0.0296 0.0430 1.0000
5.250 0.7492 0.00922 0.00310 -0.0295 0.0290 1.0000
5.500 0.7761 0.00957 0.00341 -0.0294 0.0198 1.0000
5.750 0.8029 0.00992 0.00373 -0.0293 0.0140 1.0000
6.000 0.8297 0.01027 0.00409 -0.0291 0.0104 1.0000
6.250 0.8565 0.01060 0.00445 -0.0289 0.0085 1.0000
6.500 0.8831 0.01099 0.00486 -0.0288 0.0069 1.0000
6.750 0.9095 0.01144 0.00535 -0.0285 0.0060 1.0000
7.000 0.9359 0.01184 0.00583 -0.0283 0.0055 1.0000
7.250 0.9621 0.01228 0.00633 -0.0281 0.0051 1.0000
7.500 0.9881 0.01274 0.00684 -0.0278 0.0046 1.0000
7.750 1.0137 0.01330 0.00745 -0.0276 0.0042 1.0000
8.000 1.0385 0.01406 0.00832 -0.0272 0.0038 1.0000
8.250 1.0632 0.01483 0.00919 -0.0269 0.0037 1.0000
8.500 1.0880 0.01548 0.00996 -0.0265 0.0036 1.0000
8.750 1.1125 0.01619 0.01078 -0.0261 0.0036 1.0000
9.000 1.1365 0.01697 0.01166 -0.0258 0.0035 1.0000
9.250 1.1601 0.01781 0.01262 -0.0253 0.0034 1.0000
9.500 1.1832 0.01871 0.01366 -0.0248 0.0033 1.0000
9.750 1.2056 0.01970 0.01479 -0.0243 0.0032 1.0000
10.000 1.2275 0.02076 0.01598 -0.0238 0.0031 1.0000
10.250 1.2487 0.02187 0.01727 -0.0232 0.0029 1.0000
10.500 1.2692 0.02307 0.01862 -0.0226 0.0028 1.0000
10.750 1.2889 0.02433 0.02003 -0.0220 0.0027 1.0000
11.000 1.3077 0.02566 0.02152 -0.0213 0.0026 1.0000
11.250 1.3255 0.02707 0.02309 -0.0206 0.0026 1.0000
11.500 1.3419 0.02859 0.02477 -0.0199 0.0025 1.0000
11.750 1.3563 0.03030 0.02666 -0.0191 0.0024 1.0000
12.000 1.3679 0.03228 0.02883 -0.0182 0.0024 1.0000
12.250 1.3750 0.03466 0.03142 -0.0172 0.0023 1.0000
12.500 1.3758 0.03756 0.03455 -0.0161 0.0023 1.0000
12.750 1.3656 0.04086 0.03808 -0.0146 0.0022 1.0000
13.000 1.3500 0.04541 0.04284 -0.0159 0.0022 1.0000
13.250 1.3319 0.05340 0.05105 -0.0232 0.0022 1.0000
13.500 1.3088 0.06541 0.06326 -0.0340 0.0023 1.0000
13.750 1.2737 0.07852 0.07654 -0.0425 0.0023 1.0000
14.000 1.2279 0.09258 0.09073 -0.0501 0.0024 1.0000
14.250 1.1766 0.10771 0.10598 -0.0577 0.0025 1.0000
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Polar data table (+)
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