NACA M2 (nacam2-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M2 (nacam2-il) Reynolds number: 50,000 Max Cl/Cd: 23.59 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam2-il-50000-n5.txt Download as CSV file: xf-nacam2-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M2
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.7316 0.09235 0.08528 -0.0078 1.0000 0.0509
-9.750 -0.7409 0.08658 0.07950 -0.0112 1.0000 0.0507
-9.500 -0.7532 0.08136 0.07424 -0.0135 1.0000 0.0504
-9.250 -0.7656 0.07646 0.06925 -0.0146 1.0000 0.0502
-9.000 -0.7759 0.07142 0.06402 -0.0155 1.0000 0.0502
-8.750 -0.7841 0.06639 0.05870 -0.0159 1.0000 0.0505
-8.500 -0.7897 0.06149 0.05334 -0.0157 1.0000 0.0510
-8.250 -0.7788 0.05844 0.05039 -0.0152 1.0000 0.0535
-8.000 -0.7712 0.05493 0.04662 -0.0147 1.0000 0.0553
-7.750 -0.7636 0.05082 0.04208 -0.0139 1.0000 0.0564
-7.500 -0.7528 0.04684 0.03760 -0.0130 1.0000 0.0576
-7.250 -0.7389 0.04341 0.03360 -0.0120 1.0000 0.0607
-7.000 -0.7225 0.04025 0.02966 -0.0107 1.0000 0.0639
-6.750 -0.7025 0.03737 0.02660 -0.0101 1.0000 0.0662
-6.500 -0.6806 0.03506 0.02397 -0.0094 1.0000 0.0692
-6.250 -0.6579 0.03318 0.02168 -0.0086 1.0000 0.0749
-6.000 -0.6334 0.03111 0.01927 -0.0079 1.0000 0.0784
-5.750 -0.6086 0.02932 0.01739 -0.0072 1.0000 0.0816
-5.500 -0.5834 0.02780 0.01570 -0.0065 1.0000 0.0856
-5.250 -0.5579 0.02651 0.01410 -0.0056 1.0000 0.0910
-5.000 -0.5347 0.02531 0.01297 -0.0049 1.0000 0.1001
-4.750 -0.5109 0.02417 0.01175 -0.0041 1.0000 0.1094
-4.500 -0.4873 0.02302 0.01054 -0.0032 1.0000 0.1211
-4.250 -0.4644 0.02177 0.00936 -0.0025 1.0000 0.1442
-4.000 -0.4432 0.02028 0.00831 -0.0018 1.0000 0.2078
-3.750 -0.4263 0.01874 0.00763 -0.0003 1.0000 0.3563
-3.500 -0.4128 0.01750 0.00748 0.0030 1.0000 0.5573
-3.250 -0.3949 0.01708 0.00783 0.0077 1.0000 0.7371
-3.000 -0.3640 0.01724 0.00802 0.0097 1.0000 0.8357
-2.750 -0.3202 0.01747 0.00801 0.0083 1.0000 0.8954
-2.500 -0.2679 0.01759 0.00778 0.0044 1.0000 0.9362
-2.250 -0.2114 0.01751 0.00738 -0.0013 1.0000 0.9632
-2.000 -0.1555 0.01729 0.00688 -0.0074 1.0000 0.9858
-1.750 -0.1112 0.01698 0.00639 -0.0115 1.0000 1.0000
-1.500 -0.0942 0.01670 0.00604 -0.0103 1.0000 1.0000
-1.250 -0.0774 0.01648 0.00573 -0.0090 1.0000 1.0000
-1.000 -0.0611 0.01630 0.00551 -0.0074 1.0000 1.0000
-0.750 -0.0453 0.01616 0.00534 -0.0057 1.0000 1.0000
-0.500 -0.0299 0.01607 0.00522 -0.0039 1.0000 1.0000
-0.250 -0.0149 0.01601 0.00514 -0.0020 1.0000 1.0000
0.000 0.0000 0.01599 0.00512 0.0000 1.0000 1.0000
0.250 0.0149 0.01601 0.00514 0.0020 1.0000 1.0000
0.500 0.0299 0.01607 0.00522 0.0039 1.0000 1.0000
0.750 0.0453 0.01616 0.00533 0.0057 1.0000 1.0000
1.000 0.0611 0.01630 0.00551 0.0074 1.0000 1.0000
1.250 0.0774 0.01647 0.00573 0.0090 1.0000 1.0000
1.500 0.0942 0.01670 0.00603 0.0103 1.0000 1.0000
1.750 0.1112 0.01697 0.00639 0.0115 1.0000 1.0000
2.000 0.1555 0.01729 0.00688 0.0074 0.9858 1.0000
2.250 0.2114 0.01751 0.00738 0.0013 0.9632 1.0000
2.500 0.2678 0.01759 0.00778 -0.0044 0.9362 1.0000
2.750 0.3202 0.01747 0.00801 -0.0083 0.8954 1.0000
3.000 0.3640 0.01724 0.00802 -0.0097 0.8357 1.0000
3.250 0.3949 0.01708 0.00783 -0.0077 0.7372 1.0000
3.500 0.4128 0.01750 0.00748 -0.0030 0.5576 1.0000
3.750 0.4263 0.01874 0.00763 0.0003 0.3564 1.0000
4.000 0.4432 0.02028 0.00831 0.0018 0.2078 1.0000
4.250 0.4644 0.02177 0.00936 0.0025 0.1443 1.0000
4.500 0.4873 0.02302 0.01054 0.0032 0.1211 1.0000
4.750 0.5109 0.02417 0.01175 0.0041 0.1094 1.0000
5.000 0.5347 0.02531 0.01297 0.0049 0.1001 1.0000
5.250 0.5579 0.02651 0.01410 0.0056 0.0909 1.0000
5.500 0.5834 0.02779 0.01570 0.0065 0.0856 1.0000
5.750 0.6086 0.02932 0.01739 0.0072 0.0816 1.0000
6.000 0.6334 0.03111 0.01927 0.0079 0.0784 1.0000
6.250 0.6579 0.03318 0.02168 0.0086 0.0749 1.0000
6.500 0.6806 0.03506 0.02396 0.0094 0.0692 1.0000
6.750 0.7025 0.03737 0.02659 0.0101 0.0662 1.0000
7.000 0.7225 0.04025 0.02966 0.0107 0.0639 1.0000
7.250 0.7389 0.04342 0.03360 0.0120 0.0607 1.0000
7.500 0.7528 0.04684 0.03760 0.0130 0.0576 1.0000
7.750 0.7636 0.05082 0.04208 0.0139 0.0564 1.0000
8.000 0.7713 0.05493 0.04662 0.0147 0.0553 1.0000
8.250 0.7789 0.05844 0.05039 0.0152 0.0535 1.0000
8.500 0.7897 0.06150 0.05335 0.0157 0.0510 1.0000
8.750 0.7842 0.06640 0.05871 0.0159 0.0505 1.0000
9.000 0.7760 0.07143 0.06404 0.0155 0.0502 1.0000
9.250 0.7658 0.07648 0.06927 0.0146 0.0502 1.0000
9.500 0.7535 0.08140 0.07428 0.0134 0.0504 1.0000
9.750 0.7413 0.08663 0.07955 0.0111 0.0507 1.0000
10.000 0.7320 0.09241 0.08533 0.0076 0.0509 1.0000
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Polar data table (+)
Polar graphs
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