NACA M7 AIRFOIL (m7-il)
NACA M7 AIRFOIL - NACA/Munk M-7 airfoil
| Details | Dat file | Parser | |
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(m7-il) NACA M7 AIRFOIL NACA/Munk M-7 airfoil Max thickness 6.2% at 40% chord. Max camber 4.9% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M7 AIRFOIL
16. 16.
0.0000000 0.0000000
0.0125000 0.0203300
0.0250000 0.0273700
0.0500000 0.0385400
0.0750000 0.0477100
0.1000000 0.0554800
0.1500000 0.0669200
0.2000000 0.0747600
0.3000000 0.0809400
0.4000000 0.0772200
0.5000000 0.0666000
0.6000000 0.0519800
0.7000000 0.0358600
0.8000000 0.0207400
0.9000000 0.0094200
1.0000000 0.0047000
0.0000000 0.0000000
0.0125000 -.0001600
0.0250000 0.0000700
0.0500000 0.0025400
0.0750000 0.0055100
0.1000000 0.0075800
0.1500000 0.0138200
0.2000000 0.0171600
0.3000000 0.0191400
0.4000000 0.0153200
0.5000000 0.0087000
0.6000000 0.0005800
0.7000000 -.0065400
0.8000000 -.0105600
0.9000000 -.0088800
1.0000000 0.0000000
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Polars for NACA M7 AIRFOIL (m7-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m7-il | 50,000 | 9 | 34.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m7-il | 50,000 | 5 | 36 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m7-il | 100,000 | 9 | 50.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m7-il | 100,000 | 5 | 54.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m7-il | 200,000 | 9 | 63.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m7-il | 200,000 | 5 | 68.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m7-il | 500,000 | 9 | 73.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m7-il | 500,000 | 5 | 75.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m7-il | 1,000,000 | 9 | 73 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m7-il | 1,000,000 | 5 | 84 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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