MA409 (original) (modified line 7) (ma409-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MA409 (original) (modified line 7) (ma409-il) Reynolds number: 500,000 Max Cl/Cd: 99.3 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ma409-il-500000.txt Download as CSV file: xf-ma409-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MA409 (original)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4392 0.09967 0.09754 -0.0265 1.0000 0.0186
-10.000 -0.4324 0.09747 0.09535 -0.0262 1.0000 0.0193
-9.750 -0.4287 0.09482 0.09272 -0.0265 1.0000 0.0198
-9.500 -0.4272 0.09211 0.09004 -0.0267 1.0000 0.0203
-9.250 -0.4204 0.08868 0.08662 -0.0290 0.9976 0.0210
-9.000 -0.4094 0.08456 0.08251 -0.0331 0.9930 0.0220
-8.750 -0.3994 0.08017 0.07813 -0.0378 0.9860 0.0231
-7.750 -0.3229 0.01991 0.01586 -0.1036 0.9405 0.0124
-7.500 -0.2968 0.01714 0.01257 -0.1043 0.9332 0.0124
-7.250 -0.2692 0.01517 0.01026 -0.1048 0.9270 0.0130
-7.000 -0.2420 0.01383 0.00867 -0.1049 0.9191 0.0138
-6.750 -0.2142 0.01273 0.00735 -0.1050 0.9103 0.0147
-6.500 -0.1865 0.01186 0.00627 -0.1049 0.8989 0.0158
-6.250 -0.1590 0.01127 0.00551 -0.1048 0.8853 0.0172
-6.000 -0.1316 0.01043 0.00443 -0.1046 0.8705 0.0184
-5.750 -0.1041 0.00975 0.00357 -0.1043 0.8552 0.0221
-5.500 -0.0768 0.00926 0.00303 -0.1040 0.8412 0.0341
-5.250 -0.0492 0.00942 0.00321 -0.1037 0.8288 0.0595
-5.000 -0.0217 0.00937 0.00311 -0.1036 0.8205 0.0670
-4.750 0.0061 0.00943 0.00305 -0.1035 0.8149 0.0721
-4.500 0.0335 0.00923 0.00277 -0.1033 0.8094 0.0758
-4.250 0.0609 0.00904 0.00255 -0.1032 0.8045 0.0810
-4.000 0.0886 0.00895 0.00239 -0.1032 0.8004 0.0856
-3.750 0.1162 0.00873 0.00211 -0.1031 0.7963 0.0903
-3.250 0.1716 0.00842 0.00171 -0.1029 0.7889 0.0999
-3.000 0.1994 0.00825 0.00156 -0.1029 0.7853 0.1085
-2.750 0.2272 0.00811 0.00145 -0.1028 0.7820 0.1246
-2.500 0.2549 0.00787 0.00134 -0.1028 0.7792 0.1699
-2.250 0.2825 0.00756 0.00133 -0.1030 0.7767 0.2642
-2.000 0.3102 0.00741 0.00133 -0.1030 0.7736 0.3201
-1.750 0.3377 0.00732 0.00135 -0.1029 0.7696 0.3648
-1.500 0.3652 0.00725 0.00139 -0.1029 0.7656 0.4213
-1.250 0.3925 0.00711 0.00142 -0.1028 0.7611 0.4791
-1.000 0.4184 0.00679 0.00150 -0.1025 0.7542 0.6155
-0.750 0.4445 0.00601 0.00157 -0.1016 0.7469 1.0000
-0.500 0.4719 0.00611 0.00161 -0.1015 0.7404 1.0000
-0.250 0.4994 0.00622 0.00167 -0.1013 0.7343 1.0000
0.000 0.5268 0.00630 0.00172 -0.1011 0.7270 1.0000
0.250 0.5538 0.00638 0.00178 -0.1009 0.7175 1.0000
0.500 0.5808 0.00644 0.00183 -0.1006 0.7071 1.0000
0.750 0.6079 0.00647 0.00186 -0.1004 0.6963 1.0000
1.000 0.6355 0.00640 0.00188 -0.1003 0.6785 1.0000
1.250 0.6555 0.00671 0.00172 -0.0985 0.5784 1.0000
1.500 0.6791 0.00724 0.00204 -0.0977 0.5501 1.0000
1.750 0.7057 0.00741 0.00223 -0.0975 0.5302 1.0000
2.000 0.7323 0.00753 0.00232 -0.0972 0.4894 1.0000
2.250 0.7557 0.00798 0.00246 -0.0965 0.4240 1.0000
2.500 0.7770 0.00871 0.00273 -0.0954 0.3339 1.0000
2.750 0.7985 0.00949 0.00307 -0.0945 0.2298 1.0000
3.000 0.8149 0.01106 0.00376 -0.0929 0.0718 1.0000
3.250 0.8374 0.01190 0.00436 -0.0920 0.0223 1.0000
3.500 0.8625 0.01239 0.00495 -0.0913 0.0186 1.0000
3.750 0.8866 0.01302 0.00571 -0.0905 0.0172 1.0000
4.000 0.9107 0.01362 0.00638 -0.0897 0.0164 1.0000
4.250 0.9343 0.01426 0.00711 -0.0889 0.0150 1.0000
4.500 0.9567 0.01508 0.00801 -0.0878 0.0142 1.0000
4.750 0.9783 0.01603 0.00904 -0.0866 0.0134 1.0000
5.000 0.9991 0.01715 0.01024 -0.0853 0.0128 1.0000
5.250 1.0198 0.01848 0.01165 -0.0838 0.0126 1.0000
5.500 1.0413 0.02014 0.01346 -0.0823 0.0132 1.0000
5.750 1.0643 0.02299 0.01654 -0.0806 0.0156 1.0000
13.750 0.7464 0.16685 0.16492 -0.0750 0.0135 1.0000
14.000 0.7456 0.17026 0.16834 -0.0763 0.0131 1.0000
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Polar data table (+)
Polar graphs
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