AG14 (ag14-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG14 (ag14-il) Reynolds number: 500,000 Max Cl/Cd: 76.02 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag14-il-500000-n5.txt Download as CSV file: xf-ag14-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG14
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5499 0.09708 0.09488 0.0177 1.0000 0.0077
-7.750 -0.5453 0.09326 0.09108 0.0155 1.0000 0.0076
-7.500 -0.5410 0.08932 0.08716 0.0131 1.0000 0.0074
-7.250 -0.5355 0.08279 0.08065 0.0075 1.0000 0.0054
-7.000 -0.5248 0.07799 0.07585 0.0022 1.0000 0.0052
-6.750 -0.5105 0.07285 0.07072 -0.0039 1.0000 0.0050
-6.500 -0.4928 0.06719 0.06504 -0.0109 1.0000 0.0049
-6.250 -0.4713 0.06087 0.05868 -0.0187 1.0000 0.0048
-6.000 -0.4458 0.05366 0.05138 -0.0271 1.0000 0.0047
-5.750 -0.4169 0.04540 0.04293 -0.0354 1.0000 0.0047
-5.500 -0.3856 0.03527 0.03243 -0.0426 1.0000 0.0047
-5.250 -0.3543 0.02224 0.01843 -0.0474 1.0000 0.0052
-5.000 -0.3266 0.01846 0.01405 -0.0481 1.0000 0.0055
-4.750 -0.2993 0.01587 0.01098 -0.0484 1.0000 0.0058
-4.500 -0.2729 0.01477 0.00971 -0.0485 1.0000 0.0066
-4.250 -0.2461 0.01391 0.00870 -0.0483 1.0000 0.0072
-4.000 -0.2189 0.01246 0.00699 -0.0481 1.0000 0.0072
-3.750 -0.1918 0.01134 0.00565 -0.0478 1.0000 0.0074
-3.500 -0.1649 0.01046 0.00463 -0.0475 1.0000 0.0077
-3.250 -0.1380 0.00976 0.00384 -0.0471 1.0000 0.0082
-3.000 -0.1112 0.00923 0.00322 -0.0468 1.0000 0.0091
-2.750 -0.0809 0.00872 0.00262 -0.0472 0.9973 0.0104
-2.500 -0.0458 0.00832 0.00218 -0.0487 0.9886 0.0142
-2.250 -0.0108 0.00798 0.00184 -0.0501 0.9763 0.0222
-2.000 0.0242 0.00770 0.00158 -0.0516 0.9583 0.0384
-1.750 0.0577 0.00739 0.00139 -0.0527 0.9314 0.0763
-1.500 0.0861 0.00716 0.00122 -0.0525 0.8942 0.1238
-1.250 0.1116 0.00702 0.00111 -0.0518 0.8527 0.1778
-1.000 0.1371 0.00694 0.00102 -0.0511 0.8109 0.2330
-0.750 0.1630 0.00683 0.00096 -0.0506 0.7697 0.3075
-0.500 0.1893 0.00674 0.00093 -0.0502 0.7277 0.3882
0.000 0.2420 0.00648 0.00091 -0.0495 0.6477 0.5850
0.250 0.2658 0.00606 0.00094 -0.0486 0.6097 0.7736
0.500 0.2914 0.00579 0.00090 -0.0476 0.5714 1.0000
0.750 0.3188 0.00598 0.00091 -0.0474 0.5342 1.0000
1.000 0.3461 0.00619 0.00093 -0.0472 0.4989 1.0000
1.250 0.3735 0.00639 0.00097 -0.0471 0.4647 1.0000
1.500 0.4009 0.00660 0.00103 -0.0469 0.4330 1.0000
1.750 0.4283 0.00680 0.00111 -0.0468 0.4017 1.0000
2.000 0.4557 0.00702 0.00118 -0.0467 0.3720 1.0000
2.250 0.4831 0.00724 0.00128 -0.0466 0.3429 1.0000
2.500 0.5104 0.00746 0.00138 -0.0464 0.3149 1.0000
2.750 0.5377 0.00770 0.00150 -0.0463 0.2876 1.0000
3.000 0.5650 0.00793 0.00166 -0.0462 0.2625 1.0000
3.250 0.5922 0.00819 0.00182 -0.0461 0.2364 1.0000
3.500 0.6194 0.00845 0.00199 -0.0460 0.2142 1.0000
4.000 0.6735 0.00900 0.00238 -0.0457 0.1684 1.0000
4.250 0.7004 0.00930 0.00263 -0.0455 0.1488 1.0000
4.500 0.7272 0.00961 0.00288 -0.0454 0.1279 1.0000
4.750 0.7541 0.00993 0.00315 -0.0452 0.1117 1.0000
5.000 0.7807 0.01028 0.00345 -0.0451 0.0949 1.0000
5.250 0.8073 0.01062 0.00376 -0.0449 0.0812 1.0000
5.500 0.8339 0.01099 0.00413 -0.0447 0.0682 1.0000
5.750 0.8602 0.01138 0.00450 -0.0445 0.0567 1.0000
6.000 0.8865 0.01180 0.00490 -0.0443 0.0459 1.0000
6.250 0.9125 0.01224 0.00533 -0.0440 0.0357 1.0000
6.500 0.9384 0.01271 0.00579 -0.0438 0.0272 1.0000
6.750 0.9642 0.01319 0.00633 -0.0435 0.0206 1.0000
7.000 0.9896 0.01377 0.00692 -0.0432 0.0144 1.0000
7.250 1.0147 0.01440 0.00757 -0.0429 0.0103 1.0000
7.500 1.0398 0.01505 0.00832 -0.0425 0.0082 1.0000
7.750 1.0646 0.01574 0.00910 -0.0420 0.0067 1.0000
8.000 1.0881 0.01676 0.01025 -0.0415 0.0055 1.0000
8.250 1.1113 0.01781 0.01148 -0.0409 0.0050 1.0000
8.500 1.1347 0.01872 0.01253 -0.0404 0.0046 1.0000
8.750 1.1579 0.01959 0.01358 -0.0399 0.0041 1.0000
9.000 1.1810 0.02043 0.01453 -0.0394 0.0036 1.0000
9.250 1.2031 0.02146 0.01570 -0.0388 0.0033 1.0000
9.500 1.2235 0.02279 0.01721 -0.0381 0.0031 1.0000
9.750 1.2408 0.02469 0.01935 -0.0372 0.0029 1.0000
10.000 1.2554 0.02701 0.02196 -0.0361 0.0027 1.0000
10.250 1.2723 0.02871 0.02390 -0.0352 0.0026 1.0000
10.500 1.2868 0.03070 0.02615 -0.0342 0.0025 1.0000
10.750 1.2983 0.03301 0.02875 -0.0331 0.0024 1.0000
11.000 1.3059 0.03569 0.03173 -0.0319 0.0023 1.0000
11.250 1.3086 0.03874 0.03509 -0.0306 0.0022 1.0000
11.500 1.3042 0.04217 0.03881 -0.0294 0.0022 1.0000
11.750 1.2915 0.04585 0.04273 -0.0284 0.0022 1.0000
12.000 1.2758 0.05115 0.04827 -0.0310 0.0021 1.0000
12.250 1.2590 0.05916 0.05651 -0.0381 0.0022 1.0000
12.500 1.2397 0.06949 0.06704 -0.0469 0.0022 1.0000
12.750 1.2165 0.08034 0.07803 -0.0543 0.0023 1.0000
13.000 1.1904 0.09110 0.08888 -0.0605 0.0023 1.0000
13.250 1.1638 0.10163 0.09948 -0.0659 0.0024 1.0000
13.500 1.1370 0.11217 0.11007 -0.0710 0.0025 1.0000
13.750 1.1106 0.12287 0.12081 -0.0761 0.0026 1.0000
14.000 1.0842 0.13401 0.13199 -0.0813 0.0026 1.0000
14.250 1.0588 0.14583 0.14384 -0.0869 0.0027 1.0000
14.500 0.9065 0.13140 0.12940 -0.0594 0.0029 1.0000
14.750 0.8748 0.13864 0.13672 -0.0619 0.0031 1.0000
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Polar data table (+)
Polar graphs
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