NACA M25 AIRFOIL (m25-il)
NACA M25 AIRFOIL - NACA/Munk M-25 airfoil
| Details | Dat file | Parser | |
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(m25-il) NACA M25 AIRFOIL NACA/Munk M-25 airfoil Max thickness 6.3% at 30% chord. Max camber 8.2% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M25 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125100 0.0161000
0.0250100 0.0256900
0.0500200 0.0436800
0.0750200 0.0571700
0.1000200 0.0692600
0.1500300 0.0884500
0.2000400 0.1021300
0.3000400 0.1137000
0.4000400 0.1099600
0.5000300 0.0953200
0.6000300 0.0746900
0.7000200 0.0516500
0.8000100 0.0296200
0.9000000 0.0119900
0.9500000 0.0060700
1.0000000 0.0022500
0.0000000 0.0000000
0.0125000 -.0058000
0.0250000 -.0022100
0.0500000 0.0060800
0.0750100 0.0147700
0.1000100 0.0223700
0.1500100 0.0346500
0.2000200 0.0436300
0.3000200 0.0510000
0.4000200 0.0475600
0.5000100 0.0367200
0.6000100 0.0226900
0.7000000 0.0084500
0.8000000 -.0022800
0.9000000 -.0070100
0.9500000 -.0059300
1.0000000 -.0022500
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Polars for NACA M25 AIRFOIL (m25-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m25-il | 50,000 | 9 | 6.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 50,000 | 5 | 20.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 100,000 | 9 | 53.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 100,000 | 5 | 54.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 200,000 | 9 | 78.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 200,000 | 5 | 78.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 500,000 | 9 | 102.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 500,000 | 5 | 94.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 1,000,000 | 9 | 111.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 1,000,000 | 5 | 107.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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