NACA M5 AIRFOIL (m5-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M5 AIRFOIL (m5-il) Reynolds number: 50,000 Max Cl/Cd: 34 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m5-il-50000-n5.txt Download as CSV file: xf-m5-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M5 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5875 0.10379 0.09733 0.0128 1.0000 0.1191
-8.250 -0.5874 0.09961 0.09319 0.0101 1.0000 0.1205
-8.000 -0.6073 0.08867 0.08202 -0.0056 1.0000 0.0699
-7.750 -0.6009 0.08382 0.07712 -0.0068 1.0000 0.0697
-6.750 -0.5682 0.06449 0.05707 -0.0119 1.0000 0.0697
-6.500 -0.5561 0.05983 0.05207 -0.0125 1.0000 0.0699
-6.250 -0.5399 0.05768 0.05017 -0.0118 1.0000 0.0745
-6.000 -0.5241 0.05407 0.04629 -0.0121 1.0000 0.0772
-5.750 -0.5069 0.04997 0.04182 -0.0124 1.0000 0.0770
-5.500 -0.4881 0.04615 0.03759 -0.0124 1.0000 0.0768
-5.250 -0.4676 0.04271 0.03367 -0.0123 1.0000 0.0772
-5.000 -0.4458 0.03987 0.03036 -0.0121 1.0000 0.0802
-4.750 -0.4224 0.03722 0.02705 -0.0117 1.0000 0.0833
-4.500 -0.3981 0.03475 0.02411 -0.0113 1.0000 0.0838
-4.250 -0.3731 0.03250 0.02151 -0.0110 1.0000 0.0844
-4.000 -0.3480 0.03050 0.01926 -0.0108 1.0000 0.0855
-3.750 -0.3225 0.02884 0.01740 -0.0106 1.0000 0.0870
-3.500 -0.2969 0.02740 0.01577 -0.0103 1.0000 0.0889
-3.250 -0.2717 0.02614 0.01435 -0.0100 1.0000 0.0913
-3.000 -0.2480 0.02521 0.01319 -0.0094 1.0000 0.0966
-2.750 -0.2262 0.02436 0.01233 -0.0087 1.0000 0.1020
-2.500 -0.2044 0.02366 0.01158 -0.0079 1.0000 0.1067
-2.250 -0.1717 0.02291 0.01062 -0.0090 0.9946 0.1118
-2.000 -0.1281 0.02200 0.00967 -0.0124 0.9803 0.1199
-1.750 -0.0866 0.02127 0.00891 -0.0154 0.9652 0.1358
-1.500 -0.0471 0.02051 0.00824 -0.0180 0.9500 0.1647
-1.250 0.0481 0.01718 0.00783 -0.0297 0.9572 1.0000
-1.000 0.0880 0.01723 0.00747 -0.0323 0.9361 1.0000
-0.750 0.1220 0.01733 0.00729 -0.0337 0.9141 1.0000
-0.500 0.1525 0.01745 0.00718 -0.0342 0.8938 1.0000
-0.250 0.1794 0.01759 0.00713 -0.0339 0.8745 1.0000
0.000 0.2043 0.01776 0.00713 -0.0332 0.8558 1.0000
0.250 0.2283 0.01793 0.00716 -0.0323 0.8386 1.0000
0.500 0.2516 0.01811 0.00721 -0.0312 0.8225 1.0000
0.750 0.2747 0.01830 0.00730 -0.0301 0.8069 1.0000
1.000 0.2977 0.01850 0.00740 -0.0289 0.7919 1.0000
1.250 0.3208 0.01871 0.00755 -0.0278 0.7773 1.0000
1.500 0.3440 0.01892 0.00771 -0.0268 0.7629 1.0000
1.750 0.3673 0.01915 0.00790 -0.0257 0.7489 1.0000
2.000 0.3907 0.01939 0.00814 -0.0247 0.7350 1.0000
2.250 0.4142 0.01964 0.00838 -0.0238 0.7214 1.0000
2.500 0.4377 0.01990 0.00866 -0.0228 0.7080 1.0000
2.750 0.4613 0.02017 0.00897 -0.0219 0.6947 1.0000
3.000 0.4850 0.02045 0.00929 -0.0209 0.6817 1.0000
3.250 0.5086 0.02073 0.00962 -0.0200 0.6687 1.0000
3.500 0.5323 0.02101 0.00997 -0.0190 0.6558 1.0000
3.750 0.5560 0.02130 0.01036 -0.0180 0.6430 1.0000
4.000 0.5800 0.02162 0.01080 -0.0171 0.6290 1.0000
4.250 0.6039 0.02196 0.01126 -0.0163 0.6149 1.0000
4.500 0.6278 0.02229 0.01176 -0.0154 0.6006 1.0000
4.750 0.6516 0.02261 0.01223 -0.0144 0.5856 1.0000
5.000 0.6752 0.02289 0.01265 -0.0132 0.5699 1.0000
5.250 0.6986 0.02320 0.01315 -0.0122 0.5515 1.0000
5.500 0.7218 0.02344 0.01362 -0.0110 0.5316 1.0000
5.750 0.7442 0.02350 0.01381 -0.0093 0.5067 1.0000
6.000 0.7646 0.02325 0.01358 -0.0070 0.4667 1.0000
6.250 0.7838 0.02324 0.01354 -0.0050 0.4109 1.0000
6.500 0.8031 0.02362 0.01387 -0.0034 0.3511 1.0000
6.750 0.8185 0.02471 0.01458 -0.0018 0.2466 1.0000
7.000 0.8276 0.02726 0.01626 -0.0004 0.1424 1.0000
7.250 0.8384 0.02968 0.01832 0.0008 0.1031 1.0000
7.500 0.8507 0.03172 0.02027 0.0022 0.0850 1.0000
7.750 0.8635 0.03360 0.02218 0.0036 0.0732 1.0000
8.000 0.8769 0.03552 0.02418 0.0053 0.0665 1.0000
8.250 0.8919 0.03733 0.02609 0.0068 0.0595 1.0000
8.500 0.9090 0.03937 0.02826 0.0083 0.0545 1.0000
8.750 0.9304 0.04148 0.03066 0.0097 0.0509 1.0000
9.000 0.9485 0.04371 0.03307 0.0108 0.0471 1.0000
9.250 0.9658 0.04662 0.03593 0.0116 0.0438 1.0000
9.500 0.9799 0.04944 0.03927 0.0129 0.0423 1.0000
9.750 0.9902 0.05275 0.04303 0.0141 0.0413 1.0000
10.000 0.9952 0.05625 0.04697 0.0154 0.0404 1.0000
10.250 0.9949 0.05983 0.05093 0.0166 0.0395 1.0000
10.500 0.9894 0.06346 0.05490 0.0177 0.0388 1.0000
10.750 0.9776 0.06707 0.05877 0.0188 0.0384 1.0000
11.000 0.9624 0.07117 0.06311 0.0189 0.0382 1.0000
11.250 0.9446 0.07605 0.06821 0.0175 0.0383 1.0000
11.500 0.9242 0.08189 0.07425 0.0147 0.0387 1.0000
11.750 0.9022 0.08878 0.08131 0.0106 0.0393 1.0000
12.000 0.8802 0.09661 0.08924 0.0056 0.0401 1.0000
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Polar data table (+)
Polar graphs
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