MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MA409 (smoothed) (ma409sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 140.94 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ma409sm-il-1000000.txt Download as CSV file: xf-ma409sm-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4328 0.08603 0.08447 -0.0246 1.0000 0.0120
-7.750 -0.4453 0.08412 0.08260 -0.0219 1.0000 0.0120
-7.500 -0.4576 0.08206 0.08059 -0.0196 1.0000 0.0120
-7.250 -0.4397 0.07629 0.07481 -0.0272 0.9982 0.0121
-7.000 -0.4148 0.06940 0.06790 -0.0376 0.9959 0.0121
-6.750 -0.3727 0.02172 0.01879 -0.0905 0.9875 0.0090
-6.500 -0.3406 0.01903 0.01574 -0.0930 0.9862 0.0095
-6.250 -0.3079 0.01697 0.01337 -0.0951 0.9852 0.0100
-6.000 -0.2747 0.01522 0.01133 -0.0969 0.9844 0.0104
-5.750 -0.2411 0.01364 0.00949 -0.0986 0.9837 0.0106
-5.500 -0.2072 0.01235 0.00797 -0.1002 0.9830 0.0108
-5.250 -0.1783 0.01139 0.00685 -0.1006 0.9805 0.0111
-5.000 -0.1481 0.01073 0.00608 -0.1012 0.9781 0.0115
-4.750 -0.1156 0.00999 0.00522 -0.1022 0.9764 0.0118
-4.500 -0.0820 0.00937 0.00450 -0.1035 0.9749 0.0120
-4.250 -0.0471 0.00830 0.00323 -0.1051 0.9738 0.0147
-4.000 -0.0110 0.00796 0.00286 -0.1069 0.9725 0.0178
-3.750 0.0247 0.00751 0.00239 -0.1085 0.9710 0.0258
-3.500 0.0560 0.00721 0.00211 -0.1092 0.9680 0.0363
-3.250 0.0844 0.00694 0.00188 -0.1092 0.9634 0.0508
-3.000 0.1153 0.00665 0.00168 -0.1099 0.9602 0.0761
-2.750 0.1464 0.00640 0.00152 -0.1106 0.9573 0.1039
-2.500 0.1737 0.00621 0.00140 -0.1104 0.9518 0.1286
-2.250 0.2023 0.00603 0.00128 -0.1105 0.9465 0.1505
-2.000 0.2317 0.00587 0.00115 -0.1107 0.9416 0.1733
-1.500 0.2874 0.00556 0.00099 -0.1105 0.9275 0.2327
-1.250 0.3149 0.00541 0.00092 -0.1104 0.9188 0.2705
-1.000 0.3426 0.00528 0.00088 -0.1102 0.9096 0.3093
-0.750 0.3703 0.00516 0.00084 -0.1101 0.8995 0.3503
-0.500 0.3978 0.00507 0.00081 -0.1099 0.8880 0.3889
-0.250 0.4250 0.00497 0.00080 -0.1097 0.8751 0.4349
0.000 0.4520 0.00486 0.00079 -0.1095 0.8607 0.4893
0.250 0.4784 0.00463 0.00082 -0.1092 0.8445 0.6020
0.500 0.4981 0.00396 0.00091 -0.1072 0.8266 0.8905
1.000 0.5547 0.00402 0.00090 -0.1070 0.7850 1.0000
1.250 0.5810 0.00416 0.00093 -0.1065 0.7608 1.0000
1.500 0.6070 0.00431 0.00097 -0.1060 0.7341 1.0000
1.750 0.6328 0.00449 0.00104 -0.1055 0.7050 1.0000
2.000 0.6585 0.00469 0.00111 -0.1049 0.6731 1.0000
2.250 0.6839 0.00491 0.00120 -0.1044 0.6392 1.0000
2.500 0.7094 0.00515 0.00131 -0.1038 0.6028 1.0000
2.750 0.7332 0.00556 0.00145 -0.1030 0.5432 1.0000
3.000 0.7565 0.00605 0.00165 -0.1021 0.4717 1.0000
3.250 0.7808 0.00647 0.00183 -0.1015 0.4150 1.0000
3.500 0.8044 0.00700 0.00205 -0.1008 0.3454 1.0000
3.750 0.8283 0.00751 0.00228 -0.1002 0.2831 1.0000
4.000 0.8521 0.00806 0.00256 -0.0996 0.2229 1.0000
4.250 0.8751 0.00871 0.00291 -0.0988 0.1555 1.0000
4.500 0.8968 0.00957 0.00338 -0.0979 0.0754 1.0000
4.750 0.9198 0.01028 0.00384 -0.0971 0.0302 1.0000
5.000 0.9446 0.01074 0.00427 -0.0965 0.0192 1.0000
5.250 0.9696 0.01118 0.00472 -0.0959 0.0153 1.0000
5.500 0.9931 0.01186 0.00551 -0.0949 0.0130 1.0000
5.750 1.0179 0.01228 0.00599 -0.0943 0.0125 1.0000
6.000 1.0422 0.01278 0.00655 -0.0936 0.0120 1.0000
6.250 1.0660 0.01332 0.00716 -0.0929 0.0114 1.0000
6.500 1.0900 0.01382 0.00770 -0.0922 0.0107 1.0000
6.750 1.1142 0.01424 0.00813 -0.0916 0.0098 1.0000
7.000 1.1349 0.01519 0.00915 -0.0903 0.0088 1.0000
7.250 1.1505 0.01698 0.01115 -0.0881 0.0081 1.0000
7.500 1.1739 0.01751 0.01173 -0.0874 0.0078 1.0000
7.750 1.1960 0.01825 0.01256 -0.0864 0.0074 1.0000
8.000 1.2173 0.01911 0.01350 -0.0853 0.0069 1.0000
8.250 1.2384 0.01999 0.01447 -0.0842 0.0064 1.0000
8.500 1.2597 0.02075 0.01530 -0.0832 0.0060 1.0000
8.750 1.2809 0.02140 0.01599 -0.0823 0.0056 1.0000
9.000 1.2972 0.02296 0.01767 -0.0806 0.0052 1.0000
9.250 1.3024 0.02720 0.02237 -0.0771 0.0048 1.0000
9.500 1.3192 0.02849 0.02382 -0.0755 0.0047 1.0000
9.750 1.3326 0.03031 0.02585 -0.0735 0.0046 1.0000
10.000 1.3422 0.03260 0.02840 -0.0710 0.0045 1.0000
10.250 1.3474 0.03528 0.03136 -0.0680 0.0044 1.0000
10.500 1.3470 0.03836 0.03475 -0.0645 0.0044 1.0000
10.750 1.3401 0.04154 0.03821 -0.0603 0.0043 1.0000
11.000 1.3258 0.04471 0.04163 -0.0554 0.0043 1.0000
11.250 1.3075 0.04826 0.04542 -0.0511 0.0043 1.0000
11.500 1.2865 0.05238 0.04976 -0.0479 0.0043 1.0000
11.750 1.2647 0.05706 0.05466 -0.0462 0.0043 1.0000
12.000 1.2400 0.06280 0.06061 -0.0463 0.0043 1.0000
12.250 1.2171 0.06926 0.06725 -0.0484 0.0043 1.0000
12.500 1.1927 0.07719 0.07535 -0.0527 0.0044 1.0000
12.750 1.1689 0.08652 0.08484 -0.0590 0.0044 1.0000
13.000 1.1425 0.09820 0.09666 -0.0674 0.0045 1.0000
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Polar data table (+)
Polar graphs
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