AG18 (ag18-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG18 (ag18-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.38 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag18-il-1000000.txt Download as CSV file: xf-ag18-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG18
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5738 0.11437 0.11278 0.0226 1.0000 0.0059
-9.250 -0.5713 0.11022 0.10864 0.0210 1.0000 0.0061
-9.000 -0.5668 0.10664 0.10505 0.0196 1.0000 0.0062
-8.750 -0.5618 0.10318 0.10160 0.0181 1.0000 0.0062
-8.500 -0.5567 0.09974 0.09817 0.0166 1.0000 0.0063
-8.250 -0.5517 0.09622 0.09467 0.0148 1.0000 0.0064
-8.000 -0.5468 0.09268 0.09114 0.0129 1.0000 0.0065
-7.750 -0.5420 0.08906 0.08753 0.0107 1.0000 0.0066
-7.500 -0.5369 0.08533 0.08383 0.0081 1.0000 0.0068
-7.250 -0.5277 0.08111 0.07961 0.0038 1.0000 0.0069
-7.000 -0.5149 0.07643 0.07494 -0.0018 1.0000 0.0071
-6.750 -0.4991 0.07132 0.06983 -0.0083 1.0000 0.0073
-6.500 -0.4799 0.06571 0.06421 -0.0157 1.0000 0.0075
-6.250 -0.4571 0.05950 0.05795 -0.0238 1.0000 0.0078
-6.000 -0.4309 0.05261 0.05098 -0.0321 1.0000 0.0082
-5.750 -0.4022 0.04522 0.04344 -0.0395 1.0000 0.0087
-5.500 -0.3718 0.04023 0.03831 -0.0428 1.0000 0.0097
-5.250 -0.3439 0.03435 0.03219 -0.0460 1.0000 0.0098
-5.000 -0.3153 0.01526 0.01135 -0.0519 1.0000 0.0061
-4.750 -0.2890 0.01334 0.00918 -0.0520 1.0000 0.0068
-4.500 -0.2628 0.01270 0.00845 -0.0517 1.0000 0.0075
-4.250 -0.2364 0.01170 0.00729 -0.0513 1.0000 0.0080
-4.000 -0.2101 0.01064 0.00608 -0.0509 1.0000 0.0083
-3.750 -0.1839 0.00991 0.00524 -0.0504 1.0000 0.0088
-3.500 -0.1580 0.00941 0.00468 -0.0499 1.0000 0.0094
-3.250 -0.1307 0.00855 0.00370 -0.0497 0.9998 0.0095
-3.000 -0.0939 0.00781 0.00285 -0.0515 0.9964 0.0097
-2.750 -0.0569 0.00697 0.00185 -0.0532 0.9924 0.0131
-2.500 -0.0214 0.00659 0.00146 -0.0547 0.9847 0.0237
-2.250 0.0130 0.00625 0.00124 -0.0561 0.9737 0.0559
-2.000 0.0452 0.00596 0.00109 -0.0570 0.9573 0.1020
-1.750 0.0731 0.00570 0.00097 -0.0568 0.9342 0.1579
-1.500 0.0988 0.00546 0.00087 -0.0562 0.9076 0.2292
-1.250 0.1246 0.00527 0.00080 -0.0556 0.8797 0.3027
-0.750 0.1774 0.00505 0.00073 -0.0547 0.8220 0.4355
-0.500 0.2042 0.00494 0.00070 -0.0544 0.7920 0.5095
-0.250 0.2310 0.00481 0.00070 -0.0541 0.7625 0.5964
0.000 0.2570 0.00450 0.00072 -0.0537 0.7335 0.7421
0.250 0.2811 0.00401 0.00070 -0.0524 0.7036 1.0000
0.500 0.3087 0.00416 0.00069 -0.0522 0.6713 1.0000
0.750 0.3362 0.00432 0.00070 -0.0520 0.6375 1.0000
1.000 0.3638 0.00449 0.00072 -0.0519 0.6014 1.0000
1.250 0.3913 0.00468 0.00075 -0.0517 0.5637 1.0000
1.500 0.4188 0.00488 0.00079 -0.0516 0.5245 1.0000
1.750 0.4463 0.00510 0.00086 -0.0515 0.4853 1.0000
2.000 0.4738 0.00534 0.00093 -0.0514 0.4456 1.0000
2.250 0.5012 0.00558 0.00101 -0.0513 0.4072 1.0000
2.500 0.5286 0.00580 0.00110 -0.0512 0.3724 1.0000
2.750 0.5560 0.00605 0.00121 -0.0511 0.3385 1.0000
3.000 0.5834 0.00628 0.00134 -0.0510 0.3085 1.0000
3.250 0.6108 0.00652 0.00147 -0.0509 0.2798 1.0000
3.500 0.6381 0.00677 0.00161 -0.0508 0.2518 1.0000
3.750 0.6654 0.00701 0.00176 -0.0507 0.2280 1.0000
4.000 0.6926 0.00729 0.00195 -0.0506 0.2011 1.0000
4.250 0.7197 0.00755 0.00213 -0.0505 0.1785 1.0000
4.500 0.7468 0.00783 0.00233 -0.0504 0.1555 1.0000
4.750 0.7737 0.00814 0.00255 -0.0503 0.1338 1.0000
5.000 0.8006 0.00845 0.00278 -0.0501 0.1142 1.0000
5.250 0.8273 0.00879 0.00306 -0.0500 0.0954 1.0000
5.500 0.8540 0.00911 0.00333 -0.0498 0.0798 1.0000
5.750 0.8806 0.00946 0.00363 -0.0496 0.0654 1.0000
6.000 0.9071 0.00984 0.00395 -0.0494 0.0525 1.0000
6.250 0.9334 0.01023 0.00430 -0.0492 0.0408 1.0000
6.500 0.9596 0.01063 0.00467 -0.0490 0.0311 1.0000
6.750 0.9856 0.01107 0.00512 -0.0488 0.0232 1.0000
7.000 1.0112 0.01165 0.00568 -0.0484 0.0155 1.0000
7.250 1.0369 0.01214 0.00616 -0.0482 0.0113 1.0000
7.500 1.0622 0.01275 0.00683 -0.0478 0.0080 1.0000
7.750 1.0867 0.01356 0.00770 -0.0473 0.0057 1.0000
8.000 1.1106 0.01451 0.00882 -0.0467 0.0050 1.0000
8.250 1.1353 0.01518 0.00958 -0.0462 0.0046 1.0000
8.500 1.1593 0.01594 0.01044 -0.0457 0.0042 1.0000
8.750 1.1831 0.01671 0.01134 -0.0452 0.0038 1.0000
9.000 1.2065 0.01751 0.01222 -0.0447 0.0034 1.0000
9.250 1.2244 0.01953 0.01448 -0.0436 0.0029 1.0000
9.500 1.2382 0.02236 0.01768 -0.0419 0.0027 1.0000
9.750 1.2572 0.02389 0.01941 -0.0410 0.0026 1.0000
10.000 1.2731 0.02591 0.02167 -0.0398 0.0025 1.0000
10.250 1.2857 0.02841 0.02446 -0.0384 0.0025 1.0000
10.500 1.2940 0.03139 0.02775 -0.0368 0.0025 1.0000
10.750 1.2969 0.03484 0.03153 -0.0350 0.0025 1.0000
11.000 1.2933 0.03866 0.03568 -0.0332 0.0025 1.0000
11.250 1.2811 0.04250 0.03980 -0.0310 0.0025 1.0000
11.500 1.2631 0.04663 0.04415 -0.0302 0.0025 1.0000
11.750 1.2452 0.05233 0.05006 -0.0332 0.0025 1.0000
12.000 1.2275 0.06018 0.05810 -0.0397 0.0025 1.0000
12.250 1.2095 0.06994 0.06804 -0.0480 0.0025 1.0000
12.500 1.1895 0.08049 0.07873 -0.0557 0.0025 1.0000
12.750 1.1672 0.09101 0.08934 -0.0620 0.0026 1.0000
13.000 1.1425 0.10158 0.09999 -0.0675 0.0026 1.0000
13.250 1.1163 0.11247 0.11093 -0.0728 0.0026 1.0000
13.500 1.0824 0.12540 0.12392 -0.0790 0.0027 1.0000
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Polar data table (+)
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