NACA M9 AIRFOIL (m9-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: NACA M9 AIRFOIL (m9-il) Reynolds number: 50,000 Max Cl/Cd: 30.57 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m9-il-50000-n5.txt Download as CSV file: xf-m9-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M9 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2251 0.11364 0.10797 -0.0107 1.0000 0.0897
-8.750 -0.2172 0.11119 0.10562 -0.0131 1.0000 0.0922
-8.500 -0.2124 0.10961 0.10417 -0.0163 1.0000 0.0941
-8.250 -0.2022 0.10837 0.10295 -0.0236 0.9265 0.0952
-8.000 -0.1938 0.10704 0.10156 -0.0296 0.8931 0.0956
-7.750 -0.1603 0.09851 0.09294 -0.0257 0.8776 0.1006
-7.500 -0.1507 0.09601 0.09037 -0.0268 0.8563 0.1036
-7.250 -0.1450 0.09397 0.08830 -0.0277 0.8371 0.1059
-7.000 -0.1424 0.09266 0.08695 -0.0299 0.8201 0.1087
-6.750 -0.1366 0.09147 0.08570 -0.0335 0.8051 0.1100
-6.500 -0.1268 0.08948 0.08366 -0.0372 0.7908 0.1104
-6.250 -0.1141 0.08721 0.08132 -0.0409 0.7779 0.1107
-6.000 -0.1021 0.08192 0.07603 -0.0345 0.7673 0.1151
-5.500 -0.0712 0.07371 0.06755 -0.0448 0.7456 0.0806
-5.250 -0.0561 0.07063 0.06438 -0.0455 0.7359 0.0790
-5.000 -0.0356 0.06739 0.06104 -0.0496 0.7247 0.0801
-4.750 -0.0128 0.06386 0.05733 -0.0539 0.7155 0.0811
-4.500 0.0092 0.06051 0.05385 -0.0565 0.7053 0.0810
-4.250 0.0305 0.05776 0.05101 -0.0581 0.6956 0.0833
-4.000 0.0507 0.05600 0.04915 -0.0582 0.6864 0.0874
-3.750 0.0771 0.05296 0.04593 -0.0611 0.6768 0.0887
-3.500 0.1051 0.04982 0.04252 -0.0640 0.6689 0.0916
-3.250 0.1381 0.04565 0.03796 -0.0686 0.6598 0.0948
-3.000 0.1642 0.04299 0.03504 -0.0697 0.6523 0.0969
-2.750 0.1877 0.04223 0.03422 -0.0695 0.6430 0.1018
-2.500 0.2172 0.03946 0.03106 -0.0712 0.6360 0.1061
-2.250 0.2500 0.03517 0.02609 -0.0740 0.6286 0.1114
-2.000 0.2735 0.03527 0.02623 -0.0730 0.6206 0.1163
-1.750 0.3022 0.03327 0.02381 -0.0737 0.6140 0.1221
-1.500 0.3305 0.03184 0.02204 -0.0742 0.6063 0.1302
-1.250 0.3570 0.03144 0.02147 -0.0735 0.6008 0.1376
-1.000 0.3855 0.03067 0.02048 -0.0740 0.5927 0.1463
-0.750 0.4110 0.03095 0.02071 -0.0732 0.5864 0.1556
-0.500 0.4374 0.03094 0.02061 -0.0726 0.5803 0.1641
-0.250 0.4634 0.03117 0.02078 -0.0723 0.5732 0.1759
0.000 0.4898 0.03129 0.02077 -0.0715 0.5681 0.1896
0.500 0.5436 0.03166 0.02075 -0.0710 0.5550 0.2288
0.750 0.5711 0.03156 0.02041 -0.0704 0.5504 0.2516
1.000 0.5981 0.03173 0.02042 -0.0707 0.5434 0.2744
1.250 0.6258 0.03167 0.02017 -0.0706 0.5367 0.2968
1.500 0.6545 0.03142 0.01966 -0.0702 0.5306 0.3162
1.750 0.6808 0.03155 0.01969 -0.0702 0.5207 0.3306
2.000 0.7095 0.03112 0.01907 -0.0695 0.5137 0.3498
2.250 0.7353 0.03114 0.01910 -0.0694 0.5030 0.3698
2.500 0.7632 0.03089 0.01870 -0.0689 0.4955 0.3840
2.750 0.7886 0.03119 0.01900 -0.0687 0.4864 0.3888
3.000 0.8170 0.03102 0.01865 -0.0680 0.4807 0.3899
3.250 0.8397 0.03171 0.01941 -0.0679 0.4711 0.3917
3.500 0.8668 0.03166 0.01925 -0.0671 0.4648 0.3935
3.750 0.8891 0.03228 0.01992 -0.0667 0.4556 0.3944
4.000 0.9149 0.03233 0.01990 -0.0659 0.4486 0.3946
4.250 0.9367 0.03291 0.02053 -0.0653 0.4398 0.3947
4.500 0.9612 0.03306 0.02065 -0.0644 0.4321 0.3949
4.750 0.9825 0.03361 0.02125 -0.0637 0.4231 0.3951
5.000 1.0060 0.03383 0.02147 -0.0628 0.4151 0.3955
5.250 1.0261 0.03448 0.02218 -0.0620 0.4061 0.3964
5.500 1.0489 0.03473 0.02244 -0.0611 0.3980 0.3978
5.750 1.0673 0.03549 0.02333 -0.0602 0.3887 0.3991
6.000 1.0900 0.03572 0.02355 -0.0592 0.3807 0.4005
6.250 1.1060 0.03672 0.02467 -0.0583 0.3709 0.4016
6.500 1.1289 0.03693 0.02486 -0.0573 0.3636 0.4027
6.750 1.1421 0.03824 0.02632 -0.0564 0.3542 0.4035
7.000 1.1634 0.03868 0.02678 -0.0554 0.3475 0.4045
7.250 1.1762 0.04006 0.02827 -0.0545 0.3399 0.4055
7.500 1.1912 0.04114 0.02943 -0.0535 0.3328 0.4068
7.750 1.2170 0.04117 0.02943 -0.0526 0.3282 0.4087
8.000 1.2118 0.04420 0.03272 -0.0514 0.3196 0.4095
8.250 1.2320 0.04472 0.03326 -0.0504 0.3147 0.4118
8.500 1.2372 0.04668 0.03534 -0.0493 0.3091 0.4136
8.750 1.2194 0.05058 0.03941 -0.0480 0.3026 0.4141
9.000 1.2355 0.05151 0.04042 -0.0471 0.2989 0.4173
9.250 1.2657 0.05124 0.04020 -0.0462 0.2964 0.4241
9.500 1.1499 0.06823 0.05738 -0.0504 0.2845 0.4142
9.750 1.1690 0.06885 0.05808 -0.0495 0.2823 0.4178
10.250 1.0925 0.08876 0.07811 -0.0563 0.2671 0.4149
10.500 1.1126 0.08906 0.07850 -0.0552 0.2656 0.4192
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