AG14 (ag14-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AG14 (ag14-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.8 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag14-il-1000000.txt Download as CSV file: xf-ag14-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5686 0.10140 0.09983 0.0202 1.0000 0.0059
-8.250 -0.5644 0.09772 0.09617 0.0185 1.0000 0.0060
-8.000 -0.5594 0.09428 0.09273 0.0168 1.0000 0.0061
-7.750 -0.5541 0.09086 0.08933 0.0150 1.0000 0.0062
-7.500 -0.5486 0.08733 0.08582 0.0127 1.0000 0.0063
-7.250 -0.5395 0.08342 0.08192 0.0089 1.0000 0.0064
-7.000 -0.5270 0.07913 0.07763 0.0041 1.0000 0.0065
-6.750 -0.5119 0.07452 0.07302 -0.0016 1.0000 0.0067
-6.500 -0.4940 0.06956 0.06805 -0.0079 1.0000 0.0069
-6.250 -0.4730 0.06423 0.06269 -0.0149 1.0000 0.0071
-6.000 -0.4489 0.05848 0.05690 -0.0221 1.0000 0.0074
-5.750 -0.4219 0.05230 0.05064 -0.0293 1.0000 0.0078
-5.500 -0.3925 0.04568 0.04389 -0.0358 1.0000 0.0083
-5.250 -0.3608 0.04068 0.03875 -0.0394 1.0000 0.0094
-4.500 -0.2734 0.01669 0.01308 -0.0487 1.0000 0.0077
-4.250 -0.2459 0.01451 0.01058 -0.0486 1.0000 0.0083
-4.000 -0.2186 0.01274 0.00851 -0.0484 1.0000 0.0085
-3.750 -0.1916 0.01143 0.00699 -0.0480 1.0000 0.0088
-3.500 -0.1652 0.01098 0.00647 -0.0476 1.0000 0.0094
-3.250 -0.1383 0.00966 0.00497 -0.0472 1.0000 0.0094
-3.000 -0.1113 0.00855 0.00373 -0.0468 1.0000 0.0093
-2.750 -0.0844 0.00788 0.00296 -0.0464 1.0000 0.0096
-2.500 -0.0566 0.00699 0.00190 -0.0462 1.0000 0.0120
-2.250 -0.0198 0.00670 0.00159 -0.0480 0.9961 0.0157
-2.000 0.0168 0.00628 0.00122 -0.0498 0.9903 0.0377
-1.750 0.0529 0.00595 0.00106 -0.0516 0.9808 0.0831
-1.500 0.0868 0.00563 0.00092 -0.0529 0.9639 0.1451
-1.250 0.1166 0.00534 0.00083 -0.0531 0.9348 0.2214
-1.000 0.1417 0.00517 0.00076 -0.0523 0.8955 0.2944
-0.750 0.1668 0.00504 0.00071 -0.0515 0.8538 0.3798
-0.500 0.1926 0.00491 0.00069 -0.0510 0.8115 0.4779
-0.250 0.2185 0.00465 0.00069 -0.0506 0.7688 0.6248
0.000 0.2382 0.00398 0.00071 -0.0485 0.7278 0.9017
0.250 0.2679 0.00404 0.00067 -0.0487 0.6836 1.0000
0.500 0.2951 0.00424 0.00067 -0.0484 0.6401 1.0000
0.750 0.3225 0.00444 0.00068 -0.0482 0.5987 1.0000
1.000 0.3500 0.00463 0.00070 -0.0481 0.5590 1.0000
1.250 0.3775 0.00483 0.00074 -0.0479 0.5200 1.0000
1.500 0.4051 0.00503 0.00078 -0.0478 0.4834 1.0000
1.750 0.4326 0.00524 0.00085 -0.0477 0.4480 1.0000
2.000 0.4602 0.00543 0.00091 -0.0476 0.4155 1.0000
2.250 0.4876 0.00564 0.00098 -0.0475 0.3823 1.0000
2.500 0.5151 0.00585 0.00107 -0.0474 0.3529 1.0000
2.750 0.5426 0.00607 0.00117 -0.0473 0.3218 1.0000
3.000 0.5700 0.00628 0.00129 -0.0472 0.2953 1.0000
3.250 0.5974 0.00652 0.00142 -0.0471 0.2657 1.0000
3.500 0.6247 0.00675 0.00155 -0.0470 0.2403 1.0000
3.750 0.6520 0.00700 0.00171 -0.0469 0.2156 1.0000
4.000 0.6791 0.00728 0.00187 -0.0467 0.1886 1.0000
4.250 0.7063 0.00753 0.00207 -0.0466 0.1667 1.0000
4.500 0.7333 0.00782 0.00228 -0.0465 0.1432 1.0000
4.750 0.7602 0.00814 0.00250 -0.0463 0.1221 1.0000
5.000 0.7871 0.00843 0.00274 -0.0462 0.1038 1.0000
5.250 0.8139 0.00876 0.00302 -0.0460 0.0869 1.0000
5.500 0.8406 0.00911 0.00330 -0.0459 0.0717 1.0000
5.750 0.8672 0.00946 0.00360 -0.0457 0.0579 1.0000
6.000 0.8937 0.00982 0.00393 -0.0455 0.0458 1.0000
6.250 0.9200 0.01022 0.00428 -0.0453 0.0347 1.0000
6.500 0.9463 0.01062 0.00465 -0.0451 0.0267 1.0000
6.750 0.9725 0.01104 0.00509 -0.0448 0.0198 1.0000
7.000 0.9983 0.01157 0.00562 -0.0445 0.0132 1.0000
7.250 1.0234 0.01234 0.00645 -0.0441 0.0085 1.0000
7.500 1.0489 0.01290 0.00705 -0.0437 0.0067 1.0000
7.750 1.0721 0.01419 0.00854 -0.0430 0.0051 1.0000
8.000 1.0971 0.01484 0.00929 -0.0426 0.0049 1.0000
8.250 1.1213 0.01565 0.01022 -0.0421 0.0046 1.0000
8.500 1.1450 0.01655 0.01125 -0.0415 0.0043 1.0000
8.750 1.1682 0.01751 0.01237 -0.0409 0.0041 1.0000
9.000 1.1912 0.01844 0.01341 -0.0404 0.0037 1.0000
9.250 1.2138 0.01939 0.01447 -0.0398 0.0034 1.0000
9.500 1.2334 0.02099 0.01625 -0.0390 0.0031 1.0000
9.750 1.2345 0.02672 0.02264 -0.0364 0.0027 1.0000
10.000 1.2519 0.02841 0.02454 -0.0356 0.0027 1.0000
10.250 1.2641 0.03096 0.02738 -0.0344 0.0026 1.0000
10.500 1.2704 0.03425 0.03099 -0.0330 0.0026 1.0000
10.750 1.2699 0.03813 0.03522 -0.0316 0.0026 1.0000
11.000 1.2613 0.04250 0.03990 -0.0303 0.0026 1.0000
11.250 1.2438 0.04659 0.04423 -0.0291 0.0026 1.0000
11.500 1.2239 0.05261 0.05046 -0.0326 0.0026 1.0000
11.750 1.2060 0.06172 0.05977 -0.0415 0.0026 1.0000
12.000 1.1856 0.07307 0.07129 -0.0512 0.0027 1.0000
12.250 1.1555 0.08575 0.08408 -0.0595 0.0027 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG14 (ag14-il)