MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MA409 (smoothed) (ma409sm-il) Reynolds number: 200,000 Max Cl/Cd: 81.19 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ma409sm-il-200000-n5.txt Download as CSV file: xf-ma409sm-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MA409 (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4312 0.08725 0.08373 -0.0267 1.0000 0.0152
-7.750 -0.4382 0.08439 0.08093 -0.0260 1.0000 0.0150
-7.500 -0.4449 0.08133 0.07794 -0.0259 1.0000 0.0149
-7.250 -0.4481 0.07771 0.07438 -0.0271 1.0000 0.0147
-7.000 -0.4496 0.07373 0.07045 -0.0291 1.0000 0.0146
-6.750 -0.4484 0.06924 0.06598 -0.0321 1.0000 0.0145
-6.500 -0.4427 0.06455 0.06130 -0.0358 1.0000 0.0149
-6.250 -0.4324 0.05917 0.05588 -0.0407 1.0000 0.0155
-6.000 -0.3994 0.04919 0.04572 -0.0534 0.9975 0.0162
-5.750 -0.3529 0.03189 0.02746 -0.0707 0.9949 0.0157
-5.500 -0.3165 0.02515 0.01975 -0.0762 0.9933 0.0157
-5.250 -0.2829 0.02174 0.01563 -0.0786 0.9915 0.0160
-5.000 -0.2496 0.01948 0.01288 -0.0804 0.9897 0.0166
-4.750 -0.2161 0.01784 0.01087 -0.0818 0.9879 0.0176
-4.500 -0.1823 0.01666 0.00942 -0.0832 0.9860 0.0186
-4.250 -0.1481 0.01536 0.00796 -0.0849 0.9845 0.0210
-4.000 -0.1132 0.01486 0.00734 -0.0867 0.9826 0.0255
-3.750 -0.0819 0.01410 0.00644 -0.0875 0.9791 0.0293
-3.500 -0.0487 0.01350 0.00577 -0.0887 0.9760 0.0369
-3.250 -0.0143 0.01303 0.00527 -0.0902 0.9732 0.0508
-3.000 0.0212 0.01258 0.00489 -0.0921 0.9709 0.0739
-2.750 0.0534 0.01224 0.00459 -0.0931 0.9669 0.1009
-2.500 0.0857 0.01197 0.00438 -0.0942 0.9623 0.1324
-2.250 0.1214 0.01169 0.00418 -0.0959 0.9587 0.1641
-2.000 0.1557 0.01143 0.00400 -0.0974 0.9541 0.1989
-1.750 0.1882 0.01117 0.00382 -0.0983 0.9480 0.2348
-1.500 0.2246 0.01089 0.00365 -0.1002 0.9442 0.2771
-1.250 0.2547 0.01066 0.00354 -0.1006 0.9373 0.3201
-1.000 0.2878 0.01041 0.00341 -0.1016 0.9319 0.3692
-0.750 0.3182 0.01016 0.00332 -0.1021 0.9252 0.4204
-0.500 0.3494 0.00986 0.00322 -0.1027 0.9185 0.4834
-0.250 0.3780 0.00943 0.00318 -0.1028 0.9106 0.5915
0.000 0.4049 0.00851 0.00305 -0.1015 0.9035 1.0000
0.250 0.4343 0.00848 0.00296 -0.1016 0.8930 1.0000
0.500 0.4648 0.00844 0.00287 -0.1020 0.8824 1.0000
0.750 0.4955 0.00841 0.00278 -0.1023 0.8709 1.0000
1.000 0.5256 0.00838 0.00273 -0.1025 0.8575 1.0000
1.250 0.5553 0.00837 0.00267 -0.1025 0.8420 1.0000
1.500 0.5847 0.00838 0.00264 -0.1025 0.8243 1.0000
1.750 0.6136 0.00841 0.00262 -0.1024 0.8043 1.0000
2.000 0.6418 0.00848 0.00265 -0.1022 0.7809 1.0000
2.250 0.6691 0.00859 0.00269 -0.1017 0.7544 1.0000
2.500 0.6958 0.00875 0.00275 -0.1012 0.7249 1.0000
2.750 0.7216 0.00895 0.00286 -0.1005 0.6924 1.0000
3.000 0.7468 0.00920 0.00303 -0.0996 0.6571 1.0000
3.250 0.7713 0.00950 0.00320 -0.0988 0.6200 1.0000
3.500 0.7954 0.00983 0.00342 -0.0978 0.5819 1.0000
3.750 0.8184 0.01025 0.00367 -0.0967 0.5363 1.0000
4.000 0.8379 0.01095 0.00396 -0.0950 0.4582 1.0000
4.250 0.8570 0.01175 0.00433 -0.0935 0.3720 1.0000
4.500 0.8772 0.01254 0.00479 -0.0922 0.2930 1.0000
4.750 0.8964 0.01357 0.00533 -0.0910 0.1993 1.0000
5.000 0.9140 0.01492 0.00607 -0.0897 0.0919 1.0000
5.250 0.9341 0.01603 0.00689 -0.0885 0.0444 1.0000
5.500 0.9558 0.01691 0.00773 -0.0874 0.0305 1.0000
5.750 0.9789 0.01756 0.00853 -0.0865 0.0251 1.0000
6.000 1.0001 0.01849 0.00954 -0.0854 0.0217 1.0000
6.250 1.0202 0.01955 0.01073 -0.0840 0.0200 1.0000
6.500 1.0405 0.02056 0.01187 -0.0826 0.0188 1.0000
6.750 1.0601 0.02172 0.01316 -0.0812 0.0178 1.0000
7.000 1.0805 0.02277 0.01430 -0.0799 0.0163 1.0000
7.250 1.1009 0.02372 0.01531 -0.0789 0.0146 1.0000
7.500 1.1187 0.02539 0.01712 -0.0773 0.0137 1.0000
7.750 1.1365 0.02774 0.01962 -0.0757 0.0130 1.0000
8.000 1.1568 0.02944 0.02155 -0.0744 0.0126 1.0000
8.250 1.1760 0.03150 0.02389 -0.0729 0.0121 1.0000
8.500 1.1939 0.03358 0.02627 -0.0714 0.0114 1.0000
8.750 1.2104 0.03532 0.02828 -0.0698 0.0105 1.0000
9.000 1.2253 0.03689 0.03007 -0.0682 0.0096 1.0000
9.250 1.2373 0.03890 0.03235 -0.0663 0.0092 1.0000
9.500 1.2462 0.04133 0.03506 -0.0640 0.0089 1.0000
9.750 1.2511 0.04404 0.03805 -0.0615 0.0086 1.0000
10.000 1.2505 0.04727 0.04164 -0.0586 0.0084 1.0000
10.250 1.2426 0.05082 0.04551 -0.0550 0.0083 1.0000
10.500 1.2291 0.05432 0.04932 -0.0511 0.0083 1.0000
10.750 1.2127 0.05801 0.05329 -0.0478 0.0082 1.0000
11.000 1.1955 0.06197 0.05750 -0.0455 0.0082 1.0000
11.250 1.1774 0.06639 0.06216 -0.0446 0.0082 1.0000
11.500 1.1595 0.07131 0.06730 -0.0450 0.0082 1.0000
11.750 1.1418 0.07689 0.07309 -0.0469 0.0082 1.0000
12.000 1.1241 0.08339 0.07979 -0.0503 0.0083 1.0000
12.250 1.1060 0.09110 0.08769 -0.0554 0.0083 1.0000
12.500 1.0850 0.10118 0.09791 -0.0626 0.0085 1.0000
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Polar data table (+)
Polar graphs
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