AG18 (ag18-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG18 (ag18-il) Reynolds number: 200,000 Max Cl/Cd: 60.34 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag18-il-200000-n5.txt Download as CSV file: xf-ag18-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4322 0.08737 0.08409 0.0008 1.0000 0.0153
-8.000 -0.4304 0.08331 0.08005 0.0002 1.0000 0.0142
-7.500 -0.5220 0.08831 0.08493 0.0056 1.0000 0.0148
-7.250 -0.5166 0.08412 0.08078 0.0027 1.0000 0.0135
-6.750 -0.4918 0.06916 0.06585 -0.0144 1.0000 0.0103
-6.250 -0.4511 0.05743 0.05399 -0.0276 1.0000 0.0098
-6.000 -0.4278 0.04991 0.04632 -0.0351 1.0000 0.0097
-5.750 -0.4021 0.04183 0.03795 -0.0415 1.0000 0.0097
-5.500 -0.3758 0.03330 0.02886 -0.0469 1.0000 0.0104
-5.250 -0.3528 0.03229 0.02775 -0.0480 1.0000 0.0120
-5.000 -0.3260 0.02828 0.02331 -0.0496 1.0000 0.0129
-4.750 -0.2979 0.02363 0.01799 -0.0507 1.0000 0.0126
-4.500 -0.2700 0.02043 0.01420 -0.0511 1.0000 0.0126
-4.250 -0.2425 0.01814 0.01147 -0.0510 1.0000 0.0128
-4.000 -0.2154 0.01639 0.00936 -0.0507 1.0000 0.0132
-3.750 -0.1886 0.01500 0.00774 -0.0503 1.0000 0.0140
-3.500 -0.1619 0.01386 0.00644 -0.0499 1.0000 0.0151
-3.250 -0.1354 0.01310 0.00557 -0.0495 1.0000 0.0168
-3.000 -0.1090 0.01225 0.00469 -0.0493 1.0000 0.0221
-2.750 -0.0823 0.01165 0.00396 -0.0490 1.0000 0.0265
-2.500 -0.0555 0.01101 0.00333 -0.0488 1.0000 0.0425
-2.250 -0.0289 0.01051 0.00295 -0.0486 1.0000 0.0774
-2.000 -0.0024 0.01004 0.00273 -0.0486 1.0000 0.1361
-1.750 0.0315 0.00956 0.00256 -0.0502 0.9945 0.2265
-1.500 0.0688 0.00910 0.00244 -0.0525 0.9830 0.3346
-1.250 0.1051 0.00870 0.00233 -0.0544 0.9690 0.4350
-1.000 0.1394 0.00830 0.00225 -0.0557 0.9517 0.5390
-0.750 0.1710 0.00781 0.00217 -0.0561 0.9315 0.6679
-0.500 0.2023 0.00709 0.00200 -0.0557 0.9087 1.0000
-0.250 0.2328 0.00712 0.00189 -0.0558 0.8817 1.0000
0.000 0.2608 0.00719 0.00180 -0.0554 0.8525 1.0000
0.250 0.2875 0.00728 0.00173 -0.0547 0.8218 1.0000
0.500 0.3136 0.00741 0.00169 -0.0539 0.7904 1.0000
0.750 0.3397 0.00756 0.00167 -0.0531 0.7579 1.0000
1.000 0.3657 0.00773 0.00166 -0.0524 0.7244 1.0000
1.250 0.3919 0.00792 0.00168 -0.0517 0.6896 1.0000
1.500 0.4181 0.00814 0.00171 -0.0511 0.6531 1.0000
1.750 0.4443 0.00837 0.00179 -0.0506 0.6141 1.0000
2.000 0.4705 0.00863 0.00186 -0.0501 0.5732 1.0000
2.250 0.4967 0.00892 0.00196 -0.0496 0.5313 1.0000
2.500 0.5230 0.00923 0.00208 -0.0492 0.4892 1.0000
2.750 0.5492 0.00955 0.00223 -0.0489 0.4479 1.0000
3.000 0.5756 0.00989 0.00245 -0.0486 0.4084 1.0000
3.250 0.6020 0.01024 0.00265 -0.0483 0.3707 1.0000
3.500 0.6283 0.01061 0.00289 -0.0481 0.3354 1.0000
3.750 0.6547 0.01097 0.00314 -0.0478 0.3027 1.0000
4.000 0.6810 0.01136 0.00342 -0.0476 0.2720 1.0000
4.250 0.7073 0.01175 0.00377 -0.0474 0.2429 1.0000
4.500 0.7336 0.01216 0.00411 -0.0472 0.2158 1.0000
4.750 0.7597 0.01259 0.00448 -0.0470 0.1889 1.0000
5.000 0.7858 0.01304 0.00488 -0.0467 0.1649 1.0000
5.250 0.8117 0.01351 0.00531 -0.0465 0.1414 1.0000
5.500 0.8374 0.01403 0.00584 -0.0462 0.1207 1.0000
5.750 0.8631 0.01456 0.00637 -0.0460 0.1019 1.0000
6.000 0.8883 0.01518 0.00694 -0.0457 0.0842 1.0000
6.250 0.9135 0.01580 0.00758 -0.0453 0.0702 1.0000
6.500 0.9385 0.01645 0.00826 -0.0450 0.0564 1.0000
6.750 0.9630 0.01722 0.00906 -0.0446 0.0454 1.0000
7.000 0.9871 0.01806 0.00997 -0.0441 0.0348 1.0000
7.250 1.0113 0.01888 0.01093 -0.0436 0.0276 1.0000
7.500 1.0345 0.01989 0.01205 -0.0431 0.0213 1.0000
7.750 1.0569 0.02109 0.01337 -0.0424 0.0172 1.0000
8.000 1.0780 0.02254 0.01500 -0.0416 0.0142 1.0000
8.250 1.1004 0.02358 0.01620 -0.0410 0.0115 1.0000
8.500 1.1203 0.02515 0.01796 -0.0402 0.0101 1.0000
8.750 1.1354 0.02778 0.02083 -0.0389 0.0091 1.0000
9.000 1.1530 0.02983 0.02325 -0.0378 0.0086 1.0000
9.250 1.1682 0.03230 0.02606 -0.0366 0.0082 1.0000
9.500 1.1807 0.03516 0.02932 -0.0353 0.0078 1.0000
9.750 1.1907 0.03817 0.03271 -0.0340 0.0074 1.0000
10.000 1.1993 0.04086 0.03574 -0.0328 0.0069 1.0000
10.250 1.2069 0.04318 0.03832 -0.0319 0.0063 1.0000
10.500 1.2122 0.04539 0.04073 -0.0310 0.0059 1.0000
10.750 1.2099 0.04814 0.04368 -0.0299 0.0057 1.0000
11.000 1.1987 0.05174 0.04751 -0.0292 0.0055 1.0000
11.250 1.1841 0.05656 0.05257 -0.0309 0.0055 1.0000
11.500 1.1684 0.06291 0.05917 -0.0352 0.0055 1.0000
11.750 1.1496 0.07156 0.06808 -0.0421 0.0056 1.0000
12.000 1.0791 0.09558 0.09256 -0.0590 0.0072 1.0000
12.250 1.0448 0.10982 0.10686 -0.0670 0.0079 1.0000
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Polar data table (+)
Polar graphs
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