MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MA409 (smoothed) (ma409sm-il) Reynolds number: 500,000 Max Cl/Cd: 100.86 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ma409sm-il-500000-n5.txt Download as CSV file: xf-ma409sm-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4547 0.08313 0.08090 -0.0265 1.0000 0.0074
-8.000 -0.4672 0.08051 0.07834 -0.0248 1.0000 0.0073
-7.750 -0.4776 0.07730 0.07518 -0.0244 1.0000 0.0073
-7.250 -0.4298 0.02671 0.02344 -0.0856 0.9870 0.0074
-7.000 -0.3987 0.02262 0.01878 -0.0895 0.9852 0.0076
-6.750 -0.3676 0.01885 0.01438 -0.0926 0.9838 0.0078
-6.500 -0.3360 0.01662 0.01175 -0.0945 0.9828 0.0082
-6.250 -0.3087 0.01558 0.01053 -0.0950 0.9800 0.0086
-6.000 -0.2793 0.01492 0.00977 -0.0957 0.9776 0.0092
-5.750 -0.2486 0.01405 0.00873 -0.0966 0.9756 0.0096
-5.500 -0.2169 0.01304 0.00749 -0.0977 0.9740 0.0099
-5.250 -0.1845 0.01218 0.00648 -0.0989 0.9725 0.0104
-5.000 -0.1514 0.01147 0.00563 -0.1002 0.9713 0.0110
-4.750 -0.1176 0.01091 0.00495 -0.1015 0.9702 0.0117
-4.500 -0.0888 0.01032 0.00426 -0.1018 0.9668 0.0131
-4.250 -0.0586 0.00990 0.00377 -0.1023 0.9636 0.0153
-4.000 -0.0269 0.00958 0.00340 -0.1032 0.9611 0.0181
-3.750 0.0054 0.00921 0.00304 -0.1042 0.9588 0.0248
-3.500 0.0386 0.00890 0.00273 -0.1053 0.9567 0.0336
-3.250 0.0658 0.00865 0.00249 -0.1051 0.9504 0.0445
-3.000 0.0972 0.00835 0.00223 -0.1058 0.9455 0.0637
-2.750 0.1273 0.00807 0.00203 -0.1063 0.9395 0.0873
-2.500 0.1569 0.00787 0.00186 -0.1066 0.9330 0.1069
-2.250 0.1870 0.00767 0.00171 -0.1071 0.9271 0.1304
-2.000 0.2159 0.00749 0.00158 -0.1072 0.9198 0.1522
-1.750 0.2453 0.00732 0.00147 -0.1075 0.9126 0.1779
-1.500 0.2743 0.00716 0.00137 -0.1077 0.9042 0.2061
-1.250 0.3028 0.00702 0.00129 -0.1077 0.8945 0.2349
-1.000 0.3313 0.00690 0.00122 -0.1078 0.8840 0.2663
-0.750 0.3596 0.00678 0.00116 -0.1078 0.8721 0.3008
-0.500 0.3876 0.00669 0.00113 -0.1077 0.8586 0.3360
-0.250 0.4152 0.00661 0.00110 -0.1076 0.8432 0.3730
0.000 0.4424 0.00655 0.00109 -0.1073 0.8258 0.4120
0.500 0.4958 0.00641 0.00111 -0.1067 0.7856 0.5172
0.750 0.5212 0.00619 0.00117 -0.1061 0.7626 0.6424
1.250 0.5693 0.00573 0.00125 -0.1038 0.7095 1.0000
1.500 0.5949 0.00593 0.00131 -0.1032 0.6788 1.0000
1.750 0.6203 0.00615 0.00138 -0.1026 0.6460 1.0000
2.000 0.6454 0.00640 0.00150 -0.1020 0.6119 1.0000
2.250 0.6706 0.00666 0.00161 -0.1014 0.5771 1.0000
2.500 0.6957 0.00694 0.00175 -0.1008 0.5428 1.0000
2.750 0.7211 0.00721 0.00190 -0.1003 0.5101 1.0000
3.000 0.7463 0.00750 0.00208 -0.0998 0.4776 1.0000
3.250 0.7697 0.00799 0.00230 -0.0990 0.4186 1.0000
3.500 0.7920 0.00863 0.00257 -0.0981 0.3388 1.0000
3.750 0.8151 0.00922 0.00285 -0.0973 0.2716 1.0000
4.000 0.8376 0.00994 0.00320 -0.0965 0.1972 1.0000
4.250 0.8599 0.01069 0.00363 -0.0958 0.1262 1.0000
4.500 0.8816 0.01156 0.00414 -0.0949 0.0570 1.0000
4.750 0.9056 0.01210 0.00456 -0.0942 0.0328 1.0000
5.000 0.9304 0.01253 0.00495 -0.0937 0.0228 1.0000
5.250 0.9554 0.01292 0.00537 -0.0932 0.0182 1.0000
5.500 0.9799 0.01338 0.00584 -0.0926 0.0150 1.0000
5.750 1.0035 0.01400 0.00656 -0.0917 0.0130 1.0000
6.000 1.0277 0.01448 0.00711 -0.0910 0.0122 1.0000
6.250 1.0516 0.01496 0.00765 -0.0904 0.0111 1.0000
6.500 1.0751 0.01551 0.00826 -0.0896 0.0103 1.0000
6.750 1.0980 0.01612 0.00893 -0.0888 0.0097 1.0000
7.000 1.1198 0.01686 0.00974 -0.0878 0.0090 1.0000
7.250 1.1387 0.01802 0.01104 -0.0863 0.0084 1.0000
7.500 1.1593 0.01892 0.01204 -0.0851 0.0079 1.0000
7.750 1.1816 0.01952 0.01273 -0.0842 0.0074 1.0000
8.000 1.2030 0.02025 0.01355 -0.0832 0.0068 1.0000
8.250 1.2230 0.02118 0.01459 -0.0820 0.0064 1.0000
8.500 1.2428 0.02209 0.01561 -0.0807 0.0060 1.0000
8.750 1.2623 0.02301 0.01662 -0.0795 0.0057 1.0000
9.000 1.2807 0.02403 0.01774 -0.0782 0.0054 1.0000
9.250 1.2956 0.02561 0.01950 -0.0764 0.0050 1.0000
9.500 1.3070 0.02792 0.02207 -0.0740 0.0048 1.0000
9.750 1.3219 0.02943 0.02379 -0.0722 0.0046 1.0000
10.000 1.3341 0.03130 0.02592 -0.0700 0.0045 1.0000
10.250 1.3428 0.03355 0.02846 -0.0675 0.0043 1.0000
10.500 1.3477 0.03610 0.03131 -0.0646 0.0042 1.0000
10.750 1.3478 0.03868 0.03419 -0.0611 0.0040 1.0000
11.000 1.3428 0.04133 0.03711 -0.0572 0.0039 1.0000
11.250 1.3343 0.04419 0.04025 -0.0534 0.0038 1.0000
11.500 1.3226 0.04742 0.04373 -0.0500 0.0037 1.0000
11.750 1.3087 0.05103 0.04759 -0.0474 0.0036 1.0000
12.000 1.2899 0.05558 0.05239 -0.0458 0.0036 1.0000
12.250 1.2709 0.06063 0.05768 -0.0455 0.0035 1.0000
12.500 1.2469 0.06717 0.06446 -0.0471 0.0036 1.0000
12.750 1.2221 0.07495 0.07246 -0.0507 0.0036 1.0000
13.000 1.1932 0.08494 0.08266 -0.0569 0.0037 1.0000
13.250 1.1617 0.09747 0.09538 -0.0655 0.0038 1.0000
13.750 0.9903 0.10297 0.10088 -0.0514 0.0043 1.0000
14.000 0.9624 0.11214 0.11014 -0.0558 0.0044 1.0000
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Polar data table (+)
Polar graphs
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