AG12 (ag12-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG12 (ag12-il) Reynolds number: 500,000 Max Cl/Cd: 74.62 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag12-il-500000-n5.txt Download as CSV file: xf-ag12-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG12
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5838 0.10038 0.09818 0.0195 1.0000 0.0056
-8.500 -0.5822 0.09622 0.09404 0.0175 1.0000 0.0054
-8.250 -0.5800 0.09201 0.08985 0.0152 1.0000 0.0053
-8.000 -0.5779 0.08770 0.08556 0.0126 1.0000 0.0052
-7.750 -0.5757 0.08322 0.08111 0.0094 1.0000 0.0051
-7.500 -0.5697 0.07799 0.07591 0.0041 1.0000 0.0050
-7.250 -0.5593 0.07179 0.06971 -0.0033 1.0000 0.0049
-7.000 -0.5444 0.06427 0.06216 -0.0129 1.0000 0.0048
-6.750 -0.5241 0.05439 0.05218 -0.0250 1.0000 0.0046
-6.500 -0.5009 0.03957 0.03698 -0.0379 1.0000 0.0044
-6.250 -0.4804 0.02264 0.01871 -0.0449 1.0000 0.0044
-6.000 -0.4549 0.01880 0.01426 -0.0455 1.0000 0.0048
-5.750 -0.4285 0.01669 0.01175 -0.0456 1.0000 0.0052
-5.500 -0.4018 0.01530 0.01009 -0.0456 1.0000 0.0055
-5.250 -0.3749 0.01429 0.00884 -0.0454 1.0000 0.0057
-5.000 -0.3484 0.01273 0.00705 -0.0454 1.0000 0.0063
-4.750 -0.3217 0.01219 0.00646 -0.0453 1.0000 0.0070
-4.500 -0.2948 0.01164 0.00584 -0.0451 1.0000 0.0077
-4.250 -0.2678 0.01087 0.00495 -0.0448 1.0000 0.0081
-4.000 -0.2407 0.01021 0.00419 -0.0446 1.0000 0.0086
-3.750 -0.2136 0.00969 0.00356 -0.0443 1.0000 0.0094
-3.500 -0.1865 0.00917 0.00294 -0.0441 1.0000 0.0110
-3.250 -0.1596 0.00879 0.00255 -0.0438 1.0000 0.0141
-3.000 -0.1279 0.00846 0.00223 -0.0446 0.9952 0.0224
-2.750 -0.0929 0.00814 0.00195 -0.0461 0.9841 0.0392
-2.500 -0.0578 0.00780 0.00172 -0.0477 0.9688 0.0709
-2.250 -0.0236 0.00748 0.00153 -0.0491 0.9463 0.1129
-2.000 0.0075 0.00722 0.00137 -0.0496 0.9147 0.1594
-1.750 0.0340 0.00705 0.00124 -0.0491 0.8769 0.2071
-1.500 0.0596 0.00695 0.00113 -0.0484 0.8392 0.2547
-1.250 0.0856 0.00688 0.00106 -0.0478 0.8023 0.3025
-1.000 0.1120 0.00685 0.00100 -0.0473 0.7656 0.3487
-0.750 0.1387 0.00680 0.00096 -0.0470 0.7309 0.4013
-0.500 0.1655 0.00677 0.00093 -0.0467 0.6963 0.4521
-0.250 0.1925 0.00674 0.00092 -0.0464 0.6622 0.5052
0.000 0.2194 0.00670 0.00092 -0.0461 0.6286 0.5664
0.250 0.2461 0.00662 0.00094 -0.0458 0.5962 0.6401
0.500 0.2715 0.00641 0.00098 -0.0452 0.5648 0.7478
0.750 0.2967 0.00600 0.00096 -0.0441 0.5349 1.0000
1.000 0.3243 0.00618 0.00098 -0.0440 0.5047 1.0000
1.250 0.3519 0.00636 0.00102 -0.0438 0.4753 1.0000
1.750 0.4071 0.00674 0.00114 -0.0436 0.4184 1.0000
2.000 0.4347 0.00694 0.00122 -0.0435 0.3909 1.0000
2.250 0.4622 0.00714 0.00131 -0.0434 0.3641 1.0000
2.500 0.4897 0.00735 0.00141 -0.0433 0.3377 1.0000
2.750 0.5172 0.00758 0.00153 -0.0433 0.3107 1.0000
3.000 0.5446 0.00781 0.00169 -0.0432 0.2841 1.0000
3.250 0.5719 0.00806 0.00184 -0.0431 0.2585 1.0000
3.500 0.5992 0.00833 0.00201 -0.0430 0.2323 1.0000
3.750 0.6264 0.00859 0.00219 -0.0428 0.2092 1.0000
4.000 0.6534 0.00889 0.00242 -0.0427 0.1839 1.0000
4.250 0.6805 0.00919 0.00264 -0.0426 0.1627 1.0000
4.500 0.7074 0.00952 0.00289 -0.0425 0.1396 1.0000
4.750 0.7343 0.00985 0.00316 -0.0423 0.1210 1.0000
5.000 0.7611 0.01020 0.00345 -0.0422 0.1017 1.0000
5.250 0.7877 0.01057 0.00380 -0.0420 0.0843 1.0000
5.500 0.8141 0.01098 0.00415 -0.0419 0.0681 1.0000
5.750 0.8406 0.01138 0.00452 -0.0417 0.0555 1.0000
6.000 0.8669 0.01181 0.00493 -0.0415 0.0437 1.0000
6.250 0.8929 0.01228 0.00537 -0.0412 0.0330 1.0000
6.500 0.9188 0.01276 0.00584 -0.0410 0.0246 1.0000
6.750 0.9448 0.01323 0.00638 -0.0407 0.0190 1.0000
7.000 0.9703 0.01381 0.00696 -0.0404 0.0136 1.0000
7.250 0.9956 0.01438 0.00757 -0.0401 0.0102 1.0000
7.500 1.0206 0.01507 0.00834 -0.0397 0.0080 1.0000
7.750 1.0456 0.01571 0.00908 -0.0394 0.0068 1.0000
8.000 1.0700 0.01646 0.00992 -0.0389 0.0058 1.0000
8.250 1.0923 0.01774 0.01136 -0.0383 0.0048 1.0000
8.500 1.1157 0.01865 0.01246 -0.0377 0.0046 1.0000
8.750 1.1382 0.01974 0.01371 -0.0371 0.0043 1.0000
9.000 1.1601 0.02085 0.01499 -0.0364 0.0040 1.0000
9.250 1.1820 0.02188 0.01617 -0.0359 0.0037 1.0000
9.500 1.2039 0.02284 0.01725 -0.0353 0.0034 1.0000
9.750 1.2251 0.02385 0.01839 -0.0348 0.0031 1.0000
10.000 1.2442 0.02521 0.01992 -0.0340 0.0029 1.0000
10.250 1.2607 0.02698 0.02189 -0.0331 0.0028 1.0000
10.500 1.2727 0.02939 0.02458 -0.0320 0.0027 1.0000
10.750 1.2796 0.03242 0.02794 -0.0305 0.0025 1.0000
11.000 1.2900 0.03459 0.03040 -0.0295 0.0025 1.0000
11.250 1.2963 0.03706 0.03313 -0.0283 0.0025 1.0000
11.500 1.2974 0.03988 0.03622 -0.0271 0.0024 1.0000
11.750 1.2897 0.04291 0.03948 -0.0257 0.0024 1.0000
12.000 1.2774 0.04709 0.04388 -0.0265 0.0024 1.0000
12.250 1.2640 0.05295 0.04997 -0.0305 0.0024 1.0000
12.500 1.2475 0.06111 0.05835 -0.0374 0.0024 1.0000
12.750 1.2276 0.07078 0.06821 -0.0449 0.0024 1.0000
13.000 1.2032 0.08129 0.07886 -0.0519 0.0024 1.0000
13.250 1.1766 0.09196 0.08963 -0.0580 0.0025 1.0000
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Polar data table (+)
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