MA409 (original) (modified line 7) (ma409-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MA409 (original) (modified line 7) (ma409-il) Reynolds number: 200,000 Max Cl/Cd: 72.82 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ma409-il-200000-n5.txt Download as CSV file: xf-ma409-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3269 0.10638 0.10314 -0.0282 1.0000 0.0151
-11.000 -0.3283 0.10228 0.09907 -0.0288 1.0000 0.0139
-10.750 -0.4266 0.11235 0.10886 -0.0217 1.0000 0.0162
-10.500 -0.4248 0.10828 0.10483 -0.0230 1.0000 0.0145
-10.250 -0.4271 0.10306 0.09965 -0.0251 1.0000 0.0126
-10.000 -0.4266 0.09841 0.09506 -0.0268 1.0000 0.0115
-9.750 -0.4229 0.09534 0.09203 -0.0276 1.0000 0.0111
-9.250 -0.4221 0.08931 0.08605 -0.0280 1.0000 0.0106
-9.000 -0.4275 0.08614 0.08294 -0.0278 1.0000 0.0104
-8.750 -0.4237 0.08175 0.07860 -0.0310 0.9951 0.0103
-8.500 -0.4132 0.07634 0.07321 -0.0370 0.9877 0.0101
-8.250 -0.3988 0.07012 0.06700 -0.0450 0.9798 0.0100
-8.000 -0.3813 0.06292 0.05979 -0.0549 0.9711 0.0099
-7.750 -0.3584 0.05356 0.05036 -0.0678 0.9626 0.0097
-7.500 -0.3249 0.03363 0.02977 -0.0900 0.9527 0.0092
-7.250 -0.2983 0.02617 0.02143 -0.0956 0.9454 0.0092
-7.000 -0.2685 0.02300 0.01766 -0.0978 0.9412 0.0101
-6.750 -0.2399 0.02105 0.01528 -0.0988 0.9366 0.0110
-6.500 -0.2119 0.01803 0.01167 -0.0997 0.9314 0.0116
-6.250 -0.1817 0.01618 0.00943 -0.1006 0.9274 0.0125
-6.000 -0.1526 0.01498 0.00791 -0.1009 0.9223 0.0139
-5.750 -0.1233 0.01408 0.00677 -0.1013 0.9168 0.0169
-5.500 -0.0921 0.01332 0.00578 -0.1018 0.9122 0.0203
-5.250 -0.0640 0.01264 0.00524 -0.1019 0.9052 0.0447
-5.000 -0.0335 0.01257 0.00507 -0.1023 0.8989 0.0651
-4.750 -0.0048 0.01250 0.00484 -0.1024 0.8906 0.0745
-4.500 0.0249 0.01224 0.00452 -0.1028 0.8823 0.0828
-4.250 0.0542 0.01207 0.00421 -0.1030 0.8719 0.0898
-4.000 0.0832 0.01168 0.00376 -0.1033 0.8613 0.0933
-3.750 0.1124 0.01141 0.00342 -0.1035 0.8516 0.0982
-3.250 0.1710 0.01094 0.00284 -0.1039 0.8310 0.1132
-3.000 0.1999 0.01072 0.00258 -0.1041 0.8210 0.1265
-2.750 0.2286 0.01051 0.00237 -0.1042 0.8131 0.1496
-2.500 0.2567 0.01025 0.00222 -0.1043 0.8065 0.1899
-2.250 0.2847 0.01000 0.00214 -0.1044 0.7999 0.2620
-2.000 0.3125 0.00985 0.00208 -0.1044 0.7934 0.3136
-1.500 0.3679 0.00961 0.00203 -0.1043 0.7834 0.4025
-1.250 0.3952 0.00948 0.00202 -0.1042 0.7781 0.4600
-1.000 0.4211 0.00912 0.00206 -0.1038 0.7730 0.5797
-0.750 0.4477 0.00829 0.00206 -0.1028 0.7676 1.0000
-0.500 0.4755 0.00841 0.00208 -0.1027 0.7608 1.0000
-0.250 0.5030 0.00853 0.00214 -0.1026 0.7541 1.0000
0.000 0.5305 0.00870 0.00223 -0.1024 0.7459 1.0000
0.250 0.5573 0.00886 0.00234 -0.1021 0.7350 1.0000
0.500 0.5841 0.00901 0.00246 -0.1018 0.7245 1.0000
0.750 0.6108 0.00916 0.00260 -0.1015 0.7138 1.0000
1.000 0.6373 0.00926 0.00275 -0.1012 0.7014 1.0000
1.250 0.6634 0.00924 0.00288 -0.1009 0.6797 1.0000
1.500 0.6845 0.00940 0.00270 -0.0991 0.5877 1.0000
1.750 0.7068 0.00983 0.00293 -0.0980 0.5652 1.0000
2.000 0.7316 0.01020 0.00325 -0.0974 0.5476 1.0000
2.250 0.7563 0.01050 0.00355 -0.0967 0.5028 1.0000
2.500 0.7774 0.01105 0.00377 -0.0955 0.4274 1.0000
2.750 0.7958 0.01195 0.00415 -0.0940 0.3252 1.0000
3.000 0.8137 0.01311 0.00465 -0.0926 0.1961 1.0000
3.250 0.8290 0.01486 0.00552 -0.0909 0.0383 1.0000
3.500 0.8514 0.01570 0.00628 -0.0899 0.0194 1.0000
3.750 0.8750 0.01636 0.00709 -0.0890 0.0157 1.0000
4.000 0.8977 0.01719 0.00812 -0.0880 0.0139 1.0000
4.250 0.9178 0.01841 0.00956 -0.0865 0.0126 1.0000
4.500 0.9401 0.01920 0.01043 -0.0856 0.0113 1.0000
4.750 0.9607 0.02026 0.01160 -0.0843 0.0104 1.0000
5.000 0.9805 0.02154 0.01297 -0.0828 0.0099 1.0000
5.250 1.0006 0.02296 0.01449 -0.0814 0.0095 1.0000
5.500 1.0215 0.02455 0.01619 -0.0801 0.0092 1.0000
5.750 1.0433 0.02634 0.01811 -0.0788 0.0090 1.0000
6.000 1.0649 0.02810 0.02009 -0.0778 0.0085 1.0000
6.250 1.0847 0.03003 0.02212 -0.0768 0.0076 1.0000
6.500 1.1021 0.03390 0.02624 -0.0755 0.0070 1.0000
6.750 1.1193 0.03599 0.02871 -0.0737 0.0068 1.0000
7.000 1.1339 0.03862 0.03171 -0.0717 0.0068 1.0000
7.250 1.1453 0.04156 0.03504 -0.0695 0.0067 1.0000
7.500 1.1532 0.04480 0.03866 -0.0669 0.0068 1.0000
7.750 1.1572 0.04830 0.04253 -0.0642 0.0068 1.0000
8.000 1.1569 0.05213 0.04669 -0.0614 0.0069 1.0000
9.500 1.1035 0.07120 0.06720 -0.0463 0.0075 1.0000
9.750 1.0855 0.07602 0.07226 -0.0469 0.0076 1.0000
10.000 1.0645 0.08234 0.07881 -0.0497 0.0077 1.0000
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Polar data table (+)
Polar graphs
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