AG16 (ag16-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG16 (ag16-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.34 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag16-il-1000000.txt Download as CSV file: xf-ag16-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5694 0.10135 0.09979 0.0146 1.0000 0.0093
-8.750 -0.5660 0.09711 0.09557 0.0125 1.0000 0.0093
-8.500 -0.5631 0.09275 0.09122 0.0101 1.0000 0.0094
-6.500 -0.4975 0.01975 0.01615 -0.0495 1.0000 0.0059
-6.250 -0.4715 0.01845 0.01466 -0.0494 1.0000 0.0057
-6.000 -0.4457 0.01698 0.01299 -0.0494 1.0000 0.0056
-5.750 -0.4202 0.01460 0.01028 -0.0493 1.0000 0.0056
-5.500 -0.3953 0.01111 0.00633 -0.0492 1.0000 0.0063
-5.250 -0.3690 0.01055 0.00573 -0.0490 1.0000 0.0071
-5.000 -0.3426 0.01003 0.00513 -0.0487 1.0000 0.0077
-4.750 -0.3163 0.00950 0.00453 -0.0483 1.0000 0.0082
-4.500 -0.2900 0.00900 0.00396 -0.0479 1.0000 0.0088
-4.250 -0.2639 0.00867 0.00359 -0.0475 1.0000 0.0093
-4.000 -0.2372 0.00794 0.00273 -0.0472 1.0000 0.0116
-3.750 -0.2074 0.00760 0.00236 -0.0475 0.9989 0.0148
-3.500 -0.1710 0.00711 0.00189 -0.0493 0.9956 0.0309
-3.250 -0.1355 0.00675 0.00165 -0.0510 0.9913 0.0612
-3.000 -0.1006 0.00641 0.00146 -0.0526 0.9844 0.1005
-2.750 -0.0667 0.00608 0.00130 -0.0540 0.9749 0.1486
-2.500 -0.0343 0.00580 0.00117 -0.0549 0.9611 0.1971
-2.250 -0.0055 0.00559 0.00106 -0.0550 0.9419 0.2435
-2.000 0.0209 0.00545 0.00098 -0.0544 0.9185 0.2805
-1.750 0.0468 0.00536 0.00091 -0.0538 0.8928 0.3162
-1.500 0.0731 0.00529 0.00084 -0.0532 0.8653 0.3529
-1.250 0.0998 0.00527 0.00079 -0.0528 0.8366 0.3847
-1.000 0.1267 0.00524 0.00075 -0.0524 0.8070 0.4208
-0.750 0.1538 0.00520 0.00073 -0.0522 0.7772 0.4678
-0.500 0.1811 0.00519 0.00071 -0.0519 0.7479 0.5098
0.000 0.2360 0.00514 0.00072 -0.0516 0.6895 0.6058
0.250 0.2633 0.00509 0.00074 -0.0514 0.6612 0.6651
0.500 0.2901 0.00497 0.00078 -0.0511 0.6328 0.7473
0.750 0.3118 0.00463 0.00081 -0.0494 0.6059 0.8991
1.000 0.3418 0.00463 0.00080 -0.0497 0.5773 1.0000
1.250 0.3697 0.00478 0.00083 -0.0496 0.5496 1.0000
1.500 0.3976 0.00494 0.00088 -0.0495 0.5214 1.0000
1.750 0.4255 0.00510 0.00093 -0.0495 0.4933 1.0000
2.000 0.4533 0.00528 0.00099 -0.0494 0.4653 1.0000
2.250 0.4811 0.00546 0.00106 -0.0494 0.4373 1.0000
2.500 0.5089 0.00565 0.00114 -0.0493 0.4090 1.0000
2.750 0.5366 0.00586 0.00125 -0.0492 0.3800 1.0000
3.000 0.5642 0.00608 0.00136 -0.0492 0.3504 1.0000
3.250 0.5917 0.00632 0.00148 -0.0491 0.3206 1.0000
3.500 0.6192 0.00655 0.00161 -0.0491 0.2941 1.0000
3.750 0.6466 0.00681 0.00178 -0.0490 0.2647 1.0000
4.000 0.6739 0.00708 0.00194 -0.0489 0.2360 1.0000
4.250 0.7012 0.00736 0.00212 -0.0488 0.2098 1.0000
4.500 0.7284 0.00764 0.00232 -0.0487 0.1869 1.0000
4.750 0.7554 0.00797 0.00255 -0.0486 0.1594 1.0000
5.000 0.7822 0.00832 0.00279 -0.0485 0.1335 1.0000
5.250 0.8092 0.00864 0.00304 -0.0484 0.1129 1.0000
5.500 0.8358 0.00903 0.00333 -0.0483 0.0911 1.0000
5.750 0.8621 0.00949 0.00366 -0.0481 0.0670 1.0000
6.000 0.8884 0.00992 0.00401 -0.0479 0.0486 1.0000
6.250 0.9146 0.01036 0.00440 -0.0477 0.0352 1.0000
6.500 0.9409 0.01078 0.00479 -0.0475 0.0259 1.0000
6.750 0.9671 0.01122 0.00522 -0.0473 0.0186 1.0000
7.000 0.9928 0.01176 0.00576 -0.0469 0.0123 1.0000
7.250 1.0177 0.01256 0.00659 -0.0464 0.0076 1.0000
7.500 1.0433 0.01308 0.00718 -0.0461 0.0063 1.0000
7.750 1.0681 0.01382 0.00797 -0.0457 0.0052 1.0000
8.000 1.0904 0.01513 0.00950 -0.0449 0.0045 1.0000
8.250 1.1149 0.01580 0.01027 -0.0444 0.0044 1.0000
8.500 1.1384 0.01665 0.01123 -0.0438 0.0042 1.0000
8.750 1.1613 0.01760 0.01230 -0.0432 0.0040 1.0000
9.000 1.1835 0.01863 0.01346 -0.0425 0.0039 1.0000
9.250 1.2052 0.01972 0.01469 -0.0418 0.0037 1.0000
9.500 1.2262 0.02085 0.01595 -0.0410 0.0035 1.0000
9.750 1.2470 0.02197 0.01719 -0.0403 0.0033 1.0000
10.000 1.2674 0.02305 0.01839 -0.0395 0.0031 1.0000
10.250 1.2868 0.02421 0.01968 -0.0388 0.0029 1.0000
10.500 1.3017 0.02605 0.02170 -0.0376 0.0027 1.0000
10.750 1.2971 0.03090 0.02702 -0.0348 0.0025 1.0000
11.250 1.2770 0.03956 0.03644 -0.0297 0.0024 1.0000
11.500 1.2677 0.04245 0.03953 -0.0279 0.0024 1.0000
11.750 1.2550 0.04643 0.04370 -0.0281 0.0024 1.0000
12.000 1.2394 0.05203 0.04951 -0.0311 0.0024 1.0000
12.250 1.2179 0.06016 0.05786 -0.0371 0.0024 1.0000
12.500 1.1950 0.06970 0.06758 -0.0442 0.0024 1.0000
12.750 1.1844 0.07704 0.07503 -0.0494 0.0024 1.0000
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Polar data table (+)
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