AG14 (ag14-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG14 (ag14-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.39 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag14-il-1000000-n5.txt Download as CSV file: xf-ag14-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5523 0.09573 0.09417 0.0176 1.0000 0.0055
-7.750 -0.5478 0.09189 0.09035 0.0155 1.0000 0.0055
-7.500 -0.5432 0.08799 0.08646 0.0130 1.0000 0.0055
-7.000 -0.5302 0.07451 0.07299 0.0001 1.0000 0.0029
-6.750 -0.5135 0.06821 0.06668 -0.0080 1.0000 0.0028
-6.500 -0.4922 0.06093 0.05935 -0.0173 1.0000 0.0028
-6.000 -0.4303 0.01881 0.01560 -0.0484 1.0000 0.0030
-5.750 -0.4041 0.01437 0.01044 -0.0494 1.0000 0.0034
-5.500 -0.3773 0.01355 0.00946 -0.0494 1.0000 0.0036
-5.250 -0.3504 0.01277 0.00853 -0.0493 1.0000 0.0038
-5.000 -0.3235 0.01196 0.00758 -0.0492 1.0000 0.0040
-4.750 -0.2965 0.01110 0.00657 -0.0491 1.0000 0.0042
-4.500 -0.2695 0.01034 0.00568 -0.0488 1.0000 0.0044
-4.250 -0.2426 0.00976 0.00500 -0.0486 1.0000 0.0047
-4.000 -0.2158 0.00932 0.00450 -0.0483 1.0000 0.0051
-3.500 -0.1491 0.00814 0.00309 -0.0506 0.9850 0.0054
-3.250 -0.1153 0.00769 0.00257 -0.0518 0.9708 0.0056
-3.000 -0.0830 0.00717 0.00191 -0.0525 0.9463 0.0067
-2.750 -0.0562 0.00701 0.00165 -0.0519 0.9085 0.0081
-2.500 -0.0310 0.00696 0.00142 -0.0510 0.8663 0.0095
-2.250 -0.0048 0.00690 0.00121 -0.0504 0.8252 0.0136
-2.000 0.0218 0.00687 0.00106 -0.0500 0.7851 0.0234
-1.750 0.0489 0.00685 0.00094 -0.0497 0.7456 0.0369
-1.500 0.0761 0.00680 0.00082 -0.0495 0.7077 0.0620
-1.250 0.1035 0.00674 0.00074 -0.0493 0.6691 0.0988
-1.000 0.1310 0.00671 0.00068 -0.0493 0.6318 0.1351
-0.750 0.1586 0.00666 0.00063 -0.0492 0.5965 0.1813
-0.500 0.1862 0.00663 0.00060 -0.0492 0.5625 0.2279
-0.250 0.2139 0.00657 0.00059 -0.0492 0.5293 0.2896
0.000 0.2415 0.00653 0.00059 -0.0492 0.4966 0.3491
0.250 0.2691 0.00650 0.00061 -0.0492 0.4658 0.4123
0.500 0.2967 0.00645 0.00065 -0.0492 0.4355 0.4856
0.750 0.3242 0.00635 0.00069 -0.0492 0.4079 0.5777
1.000 0.3511 0.00612 0.00075 -0.0490 0.3819 0.7130
1.500 0.4023 0.00574 0.00083 -0.0477 0.3311 1.0000
1.750 0.4300 0.00592 0.00090 -0.0476 0.3061 1.0000
2.000 0.4577 0.00610 0.00097 -0.0475 0.2829 1.0000
2.250 0.4853 0.00629 0.00105 -0.0475 0.2584 1.0000
2.500 0.5129 0.00646 0.00114 -0.0474 0.2382 1.0000
2.750 0.5404 0.00668 0.00125 -0.0473 0.2145 1.0000
3.000 0.5679 0.00686 0.00138 -0.0472 0.1967 1.0000
3.250 0.5953 0.00709 0.00151 -0.0471 0.1743 1.0000
3.500 0.6227 0.00730 0.00165 -0.0470 0.1567 1.0000
3.750 0.6501 0.00751 0.00180 -0.0469 0.1404 1.0000
4.000 0.6773 0.00778 0.00198 -0.0467 0.1211 1.0000
4.250 0.7045 0.00801 0.00218 -0.0466 0.1077 1.0000
4.500 0.7316 0.00826 0.00238 -0.0465 0.0926 1.0000
4.750 0.7587 0.00852 0.00259 -0.0463 0.0799 1.0000
5.000 0.7857 0.00880 0.00283 -0.0462 0.0679 1.0000
5.250 0.8126 0.00909 0.00310 -0.0460 0.0570 1.0000
5.500 0.8394 0.00940 0.00337 -0.0459 0.0471 1.0000
5.750 0.8661 0.00973 0.00366 -0.0457 0.0372 1.0000
6.000 0.8926 0.01008 0.00398 -0.0455 0.0283 1.0000
6.250 0.9190 0.01045 0.00433 -0.0453 0.0208 1.0000
6.500 0.9453 0.01084 0.00471 -0.0451 0.0150 1.0000
6.750 0.9714 0.01124 0.00514 -0.0449 0.0113 1.0000
7.000 0.9976 0.01165 0.00557 -0.0446 0.0083 1.0000
7.250 1.0233 0.01213 0.00606 -0.0443 0.0060 1.0000
7.500 1.0491 0.01261 0.00659 -0.0440 0.0048 1.0000
7.750 1.0747 0.01308 0.00712 -0.0437 0.0040 1.0000
8.000 1.0998 0.01367 0.00776 -0.0434 0.0031 1.0000
8.250 1.1245 0.01438 0.00857 -0.0430 0.0027 1.0000
8.500 1.1495 0.01495 0.00922 -0.0426 0.0026 1.0000
8.750 1.1741 0.01558 0.00998 -0.0422 0.0024 1.0000
9.000 1.1983 0.01627 0.01078 -0.0418 0.0023 1.0000
9.250 1.2221 0.01701 0.01163 -0.0413 0.0021 1.0000
9.500 1.2455 0.01779 0.01253 -0.0409 0.0020 1.0000
9.750 1.2685 0.01861 0.01346 -0.0404 0.0019 1.0000
10.000 1.2911 0.01946 0.01442 -0.0398 0.0017 1.0000
10.250 1.3132 0.02038 0.01546 -0.0393 0.0016 1.0000
10.500 1.3341 0.02148 0.01669 -0.0387 0.0015 1.0000
10.750 1.3520 0.02310 0.01850 -0.0378 0.0013 1.0000
11.000 1.3644 0.02563 0.02138 -0.0364 0.0012 1.0000
11.250 1.3817 0.02705 0.02298 -0.0356 0.0012 1.0000
11.500 1.3970 0.02868 0.02480 -0.0346 0.0012 1.0000
11.750 1.4100 0.03052 0.02684 -0.0336 0.0011 1.0000
12.000 1.4198 0.03263 0.02917 -0.0324 0.0011 1.0000
12.250 1.4253 0.03509 0.03186 -0.0311 0.0011 1.0000
12.500 1.4252 0.03789 0.03489 -0.0297 0.0011 1.0000
12.750 1.4151 0.04089 0.03808 -0.0277 0.0011 1.0000
13.000 1.3996 0.04526 0.04265 -0.0284 0.0011 1.0000
13.250 1.3818 0.05229 0.04990 -0.0338 0.0011 1.0000
13.500 1.3583 0.06330 0.06113 -0.0436 0.0011 1.0000
13.750 1.3259 0.07623 0.07423 -0.0525 0.0011 1.0000
14.000 1.2865 0.08938 0.08750 -0.0597 0.0011 1.0000
14.250 1.2462 0.10217 0.10036 -0.0660 0.0011 1.0000
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Polar data table (+)
Polar graphs
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