MA409 (smoothed) (ma409sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MA409 (smoothed) (ma409sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.24 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ma409sm-il-1000000-n5.txt Download as CSV file: xf-ma409sm-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4612 0.09213 0.09048 -0.0259 1.0000 0.0048
-9.000 -0.4682 0.08743 0.08581 -0.0269 1.0000 0.0048
-8.750 -0.5546 0.03089 0.02883 -0.0858 0.9902 0.0045
-8.500 -0.5307 0.01974 0.01656 -0.0959 0.9868 0.0049
-8.250 -0.5014 0.01807 0.01466 -0.0976 0.9856 0.0051
-8.000 -0.4711 0.01692 0.01333 -0.0991 0.9846 0.0053
-7.750 -0.4401 0.01590 0.01215 -0.1005 0.9838 0.0055
-7.500 -0.4089 0.01487 0.01096 -0.1019 0.9831 0.0058
-7.250 -0.3810 0.01397 0.00987 -0.1024 0.9811 0.0060
-7.000 -0.3536 0.01312 0.00887 -0.1028 0.9787 0.0062
-6.750 -0.3242 0.01229 0.00789 -0.1035 0.9769 0.0063
-6.500 -0.2940 0.01155 0.00701 -0.1043 0.9752 0.0065
-6.250 -0.2636 0.01087 0.00619 -0.1050 0.9737 0.0067
-6.000 -0.2327 0.01029 0.00551 -0.1059 0.9722 0.0069
-5.750 -0.2017 0.00983 0.00495 -0.1067 0.9708 0.0072
-5.500 -0.1720 0.00944 0.00448 -0.1072 0.9685 0.0074
-5.250 -0.1448 0.00902 0.00399 -0.1070 0.9645 0.0076
-5.000 -0.1157 0.00851 0.00337 -0.1073 0.9612 0.0080
-4.750 -0.0854 0.00808 0.00287 -0.1079 0.9585 0.0091
-4.500 -0.0553 0.00780 0.00255 -0.1084 0.9556 0.0104
-4.250 -0.0280 0.00758 0.00230 -0.1082 0.9499 0.0116
-4.000 0.0019 0.00733 0.00202 -0.1086 0.9443 0.0145
-3.750 0.0300 0.00712 0.00181 -0.1086 0.9363 0.0183
-3.500 0.0591 0.00692 0.00160 -0.1087 0.9286 0.0241
-3.250 0.0870 0.00675 0.00142 -0.1087 0.9200 0.0316
-3.000 0.1152 0.00657 0.00126 -0.1087 0.9119 0.0435
-2.750 0.1433 0.00640 0.00112 -0.1087 0.9028 0.0616
-2.500 0.1710 0.00625 0.00100 -0.1087 0.8928 0.0811
-2.250 0.1987 0.00613 0.00091 -0.1086 0.8820 0.0990
-2.000 0.2263 0.00605 0.00081 -0.1084 0.8699 0.1148
-1.750 0.2537 0.00597 0.00074 -0.1083 0.8564 0.1347
-1.500 0.2809 0.00591 0.00069 -0.1081 0.8415 0.1542
-1.250 0.3080 0.00587 0.00065 -0.1078 0.8250 0.1775
-1.000 0.3348 0.00585 0.00061 -0.1075 0.8070 0.2003
-0.750 0.3616 0.00583 0.00059 -0.1073 0.7874 0.2251
-0.500 0.3881 0.00585 0.00059 -0.1069 0.7658 0.2490
-0.250 0.4146 0.00587 0.00060 -0.1066 0.7423 0.2790
0.000 0.4410 0.00591 0.00062 -0.1062 0.7174 0.3071
0.250 0.4672 0.00597 0.00066 -0.1059 0.6902 0.3390
0.500 0.4933 0.00606 0.00071 -0.1055 0.6604 0.3694
0.750 0.5193 0.00615 0.00077 -0.1051 0.6287 0.4017
1.000 0.5454 0.00626 0.00085 -0.1048 0.5967 0.4356
1.250 0.5714 0.00635 0.00093 -0.1044 0.5641 0.4806
1.500 0.5974 0.00640 0.00103 -0.1042 0.5321 0.5475
1.750 0.6182 0.00578 0.00122 -0.1027 0.5044 0.8788
2.000 0.6451 0.00582 0.00129 -0.1024 0.4759 1.0000
2.250 0.6716 0.00602 0.00139 -0.1021 0.4501 1.0000
2.500 0.6981 0.00622 0.00150 -0.1018 0.4253 1.0000
2.750 0.7234 0.00655 0.00165 -0.1014 0.3820 1.0000
3.000 0.7468 0.00713 0.00188 -0.1007 0.3031 1.0000
3.250 0.7710 0.00763 0.00211 -0.1001 0.2430 1.0000
3.500 0.7940 0.00830 0.00241 -0.0994 0.1651 1.0000
3.750 0.8176 0.00891 0.00272 -0.0987 0.1044 1.0000
4.000 0.8419 0.00943 0.00304 -0.0982 0.0599 1.0000
4.250 0.8671 0.00983 0.00334 -0.0977 0.0364 1.0000
4.500 0.8927 0.01015 0.00361 -0.0973 0.0248 1.0000
4.750 0.9185 0.01045 0.00388 -0.0970 0.0180 1.0000
5.000 0.9440 0.01078 0.00418 -0.0965 0.0131 1.0000
5.250 0.9699 0.01105 0.00448 -0.0962 0.0117 1.0000
5.500 0.9953 0.01138 0.00482 -0.0957 0.0103 1.0000
5.750 1.0202 0.01179 0.00525 -0.0952 0.0086 1.0000
6.000 1.0449 0.01221 0.00573 -0.0946 0.0081 1.0000
6.250 1.0699 0.01258 0.00613 -0.0941 0.0078 1.0000
6.500 1.0946 0.01298 0.00658 -0.0935 0.0075 1.0000
6.750 1.1191 0.01338 0.00703 -0.0930 0.0071 1.0000
7.000 1.1436 0.01376 0.00746 -0.0924 0.0066 1.0000
7.250 1.1679 0.01415 0.00788 -0.0919 0.0061 1.0000
7.500 1.1916 0.01462 0.00837 -0.0912 0.0057 1.0000
7.750 1.2140 0.01525 0.00907 -0.0903 0.0052 1.0000
8.000 1.2345 0.01614 0.01006 -0.0891 0.0048 1.0000
8.250 1.2576 0.01663 0.01061 -0.0884 0.0047 1.0000
8.500 1.2801 0.01717 0.01122 -0.0876 0.0045 1.0000
8.750 1.3019 0.01779 0.01191 -0.0866 0.0042 1.0000
9.000 1.3231 0.01846 0.01268 -0.0856 0.0040 1.0000
9.250 1.3443 0.01909 0.01339 -0.0846 0.0037 1.0000
9.500 1.3655 0.01969 0.01405 -0.0837 0.0035 1.0000
9.750 1.3869 0.02023 0.01463 -0.0828 0.0032 1.0000
10.000 1.4078 0.02079 0.01524 -0.0818 0.0030 1.0000
10.250 1.4271 0.02153 0.01604 -0.0807 0.0028 1.0000
10.500 1.4404 0.02297 0.01766 -0.0785 0.0025 1.0000
10.750 1.4556 0.02411 0.01892 -0.0767 0.0025 1.0000
11.000 1.4708 0.02515 0.02009 -0.0750 0.0024 1.0000
11.250 1.4846 0.02628 0.02137 -0.0730 0.0024 1.0000
11.500 1.4965 0.02751 0.02275 -0.0709 0.0023 1.0000
11.750 1.5049 0.02882 0.02421 -0.0682 0.0023 1.0000
12.000 1.5099 0.03024 0.02579 -0.0650 0.0022 1.0000
12.250 1.5132 0.03175 0.02746 -0.0618 0.0022 1.0000
12.500 1.5139 0.03350 0.02938 -0.0586 0.0022 1.0000
12.750 1.5131 0.03543 0.03148 -0.0555 0.0021 1.0000
13.000 1.5099 0.03765 0.03389 -0.0527 0.0021 1.0000
13.250 1.5045 0.04023 0.03665 -0.0501 0.0021 1.0000
13.500 1.4988 0.04300 0.03959 -0.0481 0.0020 1.0000
13.750 1.4886 0.04648 0.04327 -0.0465 0.0020 1.0000
14.000 1.4777 0.05037 0.04734 -0.0457 0.0020 1.0000
14.250 1.4636 0.05506 0.05223 -0.0459 0.0020 1.0000
14.500 1.4467 0.06068 0.05804 -0.0472 0.0020 1.0000
14.750 1.4260 0.06756 0.06513 -0.0499 0.0020 1.0000
15.000 1.4038 0.07550 0.07325 -0.0538 0.0020 1.0000
15.250 1.3770 0.08511 0.08305 -0.0592 0.0020 1.0000
15.500 1.3481 0.09591 0.09402 -0.0655 0.0020 1.0000
15.750 1.3084 0.10978 0.10807 -0.0733 0.0020 1.0000
16.000 1.2694 0.12421 0.12264 -0.0811 0.0021 1.0000
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Polar data table (+)
Polar graphs
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