NACA M10 AIRFOIL (m10-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M10 AIRFOIL (m10-il) Reynolds number: 50,000 Max Cl/Cd: 34.48 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m10-il-50000-n5.txt Download as CSV file: xf-m10-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M10 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 -0.5718 0.10853 0.10186 0.0064 1.0000 0.0961
-8.250 -0.5784 0.10573 0.09915 0.0003 1.0000 0.0973
-8.000 -0.5779 0.10209 0.09552 -0.0061 1.0000 0.0977
-7.750 -0.5649 0.09622 0.08971 -0.0023 1.0000 0.0995
-7.500 -0.5564 0.09188 0.08539 -0.0029 1.0000 0.1013
-7.250 -0.5490 0.08759 0.08110 -0.0055 1.0000 0.1022
-7.000 -0.5327 0.07817 0.07129 -0.0189 1.0000 0.0550
-6.750 -0.5217 0.07342 0.06651 -0.0198 1.0000 0.0545
-6.500 -0.5085 0.06855 0.06144 -0.0227 1.0000 0.0548
-6.000 -0.4778 0.05897 0.05134 -0.0263 1.0000 0.0551
-5.750 -0.4611 0.05435 0.04652 -0.0270 1.0000 0.0547
-5.500 -0.4420 0.04980 0.04152 -0.0279 1.0000 0.0548
-5.250 -0.4259 0.04703 0.03887 -0.0278 1.0000 0.0598
-5.000 -0.4043 0.04347 0.03493 -0.0283 1.0000 0.0632
-4.750 -0.3809 0.03960 0.03054 -0.0287 1.0000 0.0640
-4.500 -0.3560 0.03621 0.02647 -0.0287 1.0000 0.0671
-4.250 -0.3326 0.03371 0.02365 -0.0286 1.0000 0.0729
-4.000 -0.3072 0.03114 0.02063 -0.0283 1.0000 0.0745
-3.750 -0.2811 0.02887 0.01787 -0.0279 1.0000 0.0763
-3.500 -0.2547 0.02694 0.01550 -0.0273 1.0000 0.0787
-3.250 -0.2281 0.02537 0.01348 -0.0267 1.0000 0.0823
-3.000 -0.2036 0.02419 0.01225 -0.0263 1.0000 0.0907
-2.750 -0.1774 0.02302 0.01079 -0.0257 1.0000 0.0953
-2.500 -0.1506 0.02195 0.00949 -0.0250 1.0000 0.0979
-2.250 -0.1250 0.02098 0.00847 -0.0244 1.0000 0.1018
-2.000 -0.1004 0.02021 0.00760 -0.0237 1.0000 0.1074
-1.750 -0.0766 0.01952 0.00681 -0.0229 1.0000 0.1153
-1.500 -0.0531 0.01886 0.00617 -0.0222 1.0000 0.1299
-1.250 -0.0299 0.01808 0.00562 -0.0217 1.0000 0.1691
-1.000 0.0122 0.01497 0.00518 -0.0238 1.0000 1.0000
-0.750 0.0321 0.01507 0.00497 -0.0226 1.0000 1.0000
-0.500 0.0514 0.01520 0.00489 -0.0214 1.0000 1.0000
-0.250 0.0704 0.01539 0.00491 -0.0203 1.0000 1.0000
0.000 0.0893 0.01562 0.00500 -0.0193 1.0000 1.0000
0.250 0.1142 0.01589 0.00514 -0.0196 0.9962 1.0000
0.500 0.1590 0.01611 0.00524 -0.0237 0.9797 1.0000
0.750 0.2042 0.01632 0.00538 -0.0277 0.9639 1.0000
1.000 0.2478 0.01649 0.00553 -0.0312 0.9469 1.0000
1.250 0.2896 0.01665 0.00571 -0.0343 0.9293 1.0000
1.500 0.3302 0.01679 0.00590 -0.0369 0.9116 1.0000
1.750 0.3657 0.01696 0.00612 -0.0383 0.8913 1.0000
2.000 0.4001 0.01711 0.00635 -0.0394 0.8715 1.0000
2.250 0.4311 0.01730 0.00665 -0.0397 0.8507 1.0000
2.500 0.4604 0.01749 0.00693 -0.0395 0.8299 1.0000
2.750 0.4875 0.01771 0.00726 -0.0389 0.8086 1.0000
3.000 0.5140 0.01794 0.00765 -0.0381 0.7875 1.0000
3.250 0.5393 0.01820 0.00805 -0.0371 0.7655 1.0000
3.500 0.5645 0.01845 0.00844 -0.0359 0.7438 1.0000
3.750 0.5889 0.01873 0.00895 -0.0347 0.7200 1.0000
4.000 0.6131 0.01899 0.00941 -0.0333 0.6954 1.0000
4.250 0.6345 0.01908 0.00958 -0.0306 0.6563 1.0000
4.500 0.6496 0.01898 0.00922 -0.0261 0.5693 1.0000
4.750 0.6665 0.01933 0.00924 -0.0229 0.4641 1.0000
5.000 0.6841 0.02024 0.00973 -0.0206 0.3308 1.0000
5.250 0.6978 0.02308 0.01119 -0.0195 0.1346 1.0000
5.500 0.7173 0.02509 0.01292 -0.0187 0.0960 1.0000
5.750 0.7371 0.02687 0.01477 -0.0175 0.0821 1.0000
6.000 0.7569 0.02860 0.01657 -0.0164 0.0681 1.0000
6.250 0.7786 0.03051 0.01867 -0.0149 0.0612 1.0000
6.500 0.8005 0.03251 0.02081 -0.0139 0.0536 1.0000
6.750 0.8250 0.03488 0.02346 -0.0127 0.0487 1.0000
7.000 0.8493 0.03751 0.02645 -0.0117 0.0455 1.0000
7.250 0.8701 0.04015 0.02928 -0.0110 0.0416 1.0000
7.500 0.8889 0.04354 0.03309 -0.0101 0.0391 1.0000
7.750 0.9059 0.04714 0.03729 -0.0089 0.0381 1.0000
8.000 0.9190 0.05108 0.04180 -0.0077 0.0376 1.0000
8.250 0.9279 0.05523 0.04648 -0.0066 0.0370 1.0000
8.500 0.9324 0.05949 0.05123 -0.0057 0.0364 1.0000
8.750 0.9325 0.06386 0.05602 -0.0050 0.0357 1.0000
9.000 0.9281 0.06834 0.06084 -0.0046 0.0353 1.0000
9.250 0.9192 0.07293 0.06570 -0.0046 0.0352 1.0000
9.500 0.9053 0.07755 0.07051 -0.0050 0.0354 1.0000
9.750 0.8882 0.08259 0.07567 -0.0068 0.0359 1.0000
10.000 0.8721 0.08858 0.08174 -0.0105 0.0366 1.0000
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Polar data table (+)
Polar graphs
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