AG16 (ag16-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AG16 (ag16-il) Reynolds number: 500,000 Max Cl/Cd: 82.4 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag16-il-500000.txt Download as CSV file: xf-ag16-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG16
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4684 0.08352 0.08150 -0.0022 1.0000 0.0165
-8.500 -0.4676 0.07950 0.07750 -0.0032 1.0000 0.0168
-8.250 -0.4677 0.07537 0.07338 -0.0044 1.0000 0.0171
-8.000 -0.4686 0.07107 0.06910 -0.0059 1.0000 0.0173
-7.750 -0.4707 0.06653 0.06458 -0.0078 1.0000 0.0175
-7.500 -0.4737 0.06190 0.05998 -0.0101 1.0000 0.0178
-7.250 -0.4760 0.05638 0.05448 -0.0145 1.0000 0.0180
-7.000 -0.4734 0.04918 0.04728 -0.0226 1.0000 0.0182
-6.750 -0.4676 0.03915 0.03714 -0.0339 1.0000 0.0182
-6.500 -0.4580 0.03100 0.02876 -0.0405 1.0000 0.0187
-6.250 -0.4444 0.02486 0.02234 -0.0442 1.0000 0.0196
-6.000 -0.4275 0.01979 0.01692 -0.0464 1.0000 0.0205
-5.750 -0.4221 0.01802 0.01309 -0.0495 1.0000 0.0103
-5.500 -0.3964 0.01591 0.01069 -0.0493 1.0000 0.0108
-5.250 -0.3703 0.01464 0.00924 -0.0491 1.0000 0.0116
-5.000 -0.3440 0.01352 0.00797 -0.0488 1.0000 0.0124
-4.750 -0.3178 0.01270 0.00704 -0.0484 1.0000 0.0135
-4.500 -0.2916 0.01218 0.00645 -0.0480 1.0000 0.0149
-4.250 -0.2654 0.01139 0.00556 -0.0475 1.0000 0.0155
-4.000 -0.2387 0.00984 0.00383 -0.0473 1.0000 0.0185
-3.750 -0.2121 0.00934 0.00328 -0.0469 1.0000 0.0233
-3.500 -0.1851 0.00866 0.00263 -0.0467 1.0000 0.0445
-3.250 -0.1586 0.00816 0.00231 -0.0466 1.0000 0.0888
-3.000 -0.1321 0.00776 0.00212 -0.0465 1.0000 0.1411
-2.750 -0.1056 0.00744 0.00199 -0.0465 1.0000 0.1963
-2.500 -0.0752 0.00714 0.00189 -0.0472 0.9985 0.2537
-2.250 -0.0357 0.00687 0.00177 -0.0498 0.9932 0.3099
-2.000 0.0026 0.00662 0.00167 -0.0521 0.9860 0.3618
-1.750 0.0399 0.00640 0.00158 -0.0541 0.9769 0.4102
-1.500 0.0756 0.00620 0.00149 -0.0556 0.9648 0.4577
-1.250 0.1080 0.00598 0.00144 -0.0564 0.9480 0.5141
-1.000 0.1370 0.00580 0.00138 -0.0563 0.9270 0.5673
-0.750 0.1627 0.00563 0.00134 -0.0555 0.9016 0.6251
-0.500 0.1873 0.00544 0.00130 -0.0544 0.8744 0.6950
-0.250 0.2098 0.00517 0.00128 -0.0527 0.8459 0.7962
0.000 0.2357 0.00485 0.00120 -0.0514 0.8167 1.0000
0.250 0.2624 0.00498 0.00117 -0.0510 0.7862 1.0000
0.500 0.2893 0.00512 0.00115 -0.0505 0.7552 1.0000
0.750 0.3164 0.00528 0.00115 -0.0502 0.7246 1.0000
1.000 0.3435 0.00544 0.00116 -0.0498 0.6941 1.0000
1.250 0.3708 0.00561 0.00118 -0.0496 0.6635 1.0000
1.500 0.3981 0.00578 0.00123 -0.0493 0.6330 1.0000
1.750 0.4255 0.00597 0.00128 -0.0491 0.6024 1.0000
2.000 0.4528 0.00616 0.00134 -0.0489 0.5718 1.0000
2.500 0.5076 0.00657 0.00151 -0.0486 0.5102 1.0000
2.750 0.5349 0.00679 0.00164 -0.0484 0.4789 1.0000
3.000 0.5622 0.00703 0.00176 -0.0483 0.4474 1.0000
3.250 0.5894 0.00728 0.00189 -0.0481 0.4149 1.0000
3.500 0.6166 0.00755 0.00205 -0.0480 0.3817 1.0000
4.000 0.6707 0.00814 0.00243 -0.0477 0.3170 1.0000
4.250 0.6976 0.00847 0.00265 -0.0476 0.2836 1.0000
4.500 0.7243 0.00883 0.00289 -0.0475 0.2516 1.0000
4.750 0.7511 0.00919 0.00315 -0.0473 0.2214 1.0000
5.000 0.7777 0.00956 0.00345 -0.0472 0.1937 1.0000
5.250 0.8041 0.00998 0.00376 -0.0470 0.1634 1.0000
5.500 0.8304 0.01044 0.00411 -0.0468 0.1344 1.0000
5.750 0.8565 0.01092 0.00449 -0.0467 0.1081 1.0000
6.000 0.8823 0.01145 0.00492 -0.0464 0.0828 1.0000
6.250 0.9078 0.01205 0.00545 -0.0462 0.0595 1.0000
6.500 0.9329 0.01273 0.00604 -0.0458 0.0414 1.0000
6.750 0.9582 0.01339 0.00669 -0.0455 0.0292 1.0000
7.000 0.9828 0.01419 0.00750 -0.0450 0.0200 1.0000
7.250 1.0053 0.01557 0.00898 -0.0442 0.0133 1.0000
7.500 1.0302 0.01624 0.00975 -0.0437 0.0115 1.0000
7.750 1.0537 0.01720 0.01082 -0.0431 0.0099 1.0000
8.000 1.0748 0.01865 0.01239 -0.0422 0.0088 1.0000
8.250 1.0917 0.02110 0.01513 -0.0407 0.0082 1.0000
8.500 1.1083 0.02372 0.01802 -0.0393 0.0079 1.0000
8.750 1.1315 0.02445 0.01889 -0.0387 0.0074 1.0000
9.000 1.1521 0.02574 0.02036 -0.0379 0.0070 1.0000
9.250 1.1692 0.02783 0.02270 -0.0367 0.0067 1.0000
9.500 1.1842 0.03021 0.02537 -0.0354 0.0065 1.0000
9.750 1.1967 0.03283 0.02828 -0.0341 0.0063 1.0000
10.000 1.2059 0.03569 0.03144 -0.0326 0.0061 1.0000
10.250 1.2111 0.03877 0.03483 -0.0311 0.0059 1.0000
10.500 1.2100 0.04231 0.03869 -0.0294 0.0058 1.0000
10.750 1.2017 0.04587 0.04252 -0.0275 0.0058 1.0000
11.000 1.1856 0.04978 0.04668 -0.0262 0.0058 1.0000
11.250 1.1645 0.05534 0.05250 -0.0279 0.0058 1.0000
11.500 1.1432 0.06257 0.05997 -0.0329 0.0059 1.0000
11.750 1.1223 0.07132 0.06893 -0.0399 0.0060 1.0000
12.000 1.0991 0.08180 0.07959 -0.0482 0.0062 1.0000
12.250 1.0735 0.09352 0.09145 -0.0564 0.0064 1.0000
12.500 1.0442 0.10651 0.10455 -0.0642 0.0067 1.0000
12.750 1.0084 0.12146 0.11955 -0.0717 0.0071 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG16 (ag16-il)