NACA M23 AIRFOIL (m23-il)
NACA M23 AIRFOIL - NACA/Munk M-23 airfoil
| Details | Dat file | Parser | |
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(m23-il) NACA M23 AIRFOIL NACA/Munk M-23 airfoil Max thickness 8.1% at 30.1% chord. Max camber 6.4% at 30.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA M23 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125900 0.0172300
0.0251400 0.0274700
0.0502300 0.0433400
0.0752900 0.0560100
0.1003500 0.0667800
0.1504300 0.0833200
0.2004900 0.0946600
0.3005400 0.1045400
0.4005300 0.1011200
0.5004600 0.0882000
0.6003600 0.0695800
0.7002500 0.0484600
0.8001500 0.0280400
0.9000599 0.0119200
0.9500300 0.0061600
1.0000000 0.0027000
0.0000000 0.0000000
0.0124500 -.0086600
0.0249600 -.0076300
0.0499800 -.0035600
0.0750100 0.0010100
0.1000300 0.0056800
0.1500700 0.0135200
0.2001000 0.0188600
0.3001200 0.0231400
0.4001000 0.0198200
0.5000600 0.0117000
0.6000100 0.0021800
0.6999600 -.0070400
0.7999400 -.0124600
0.8999400 -.0116800
0.9499600 -.0082400
1.0000000 -.0027000
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Polars for NACA M23 AIRFOIL (m23-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m23-il | 50,000 | 9 | 6.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m23-il | 50,000 | 5 | 23.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m23-il | 100,000 | 9 | 44.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m23-il | 100,000 | 5 | 53.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m23-il | 200,000 | 9 | 76.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m23-il | 200,000 | 5 | 76 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m23-il | 500,000 | 9 | 106.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m23-il | 500,000 | 5 | 102.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m23-il | 1,000,000 | 9 | 128.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m23-il | 1,000,000 | 5 | 117.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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