USA 27 mod. AIRFOIL (usa27m2-il)
USA 27 mod. AIRFOIL - USA-27MOD airfoil
| Details | Dat file | Parser | |
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(usa27m2-il) USA 27 mod. AIRFOIL USA-27MOD airfoil Max thickness 13.3% at 30% chord. Max camber 5% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
USA 27 mod. AIRFOIL
17. 17.
0.0000000 0.0008300
0.0125000 0.0237100
0.0250000 0.0372400
0.0500000 0.0585800
0.0750000 0.0732700
0.1000000 0.0846300
0.1500000 0.0994000
0.2000000 0.1096100
0.3000000 0.1167600
0.4000000 0.1143700
0.5000000 0.1070700
0.6000000 0.0943600
0.7000000 0.0792000
0.8000000 0.0583600
0.9000000 0.0329700
0.9500000 0.0179100
1.0000000 0.0002200
0.0000000 0.0008300
0.0125000 -.0159000
0.0250000 -.0184600
0.0500000 -.0219600
0.0750000 -.0239600
0.1000000 -.0255600
0.1500000 -.0254400
0.2000000 -.0229100
0.3000000 -.0161200
0.4000000 -.0123900
0.5000000 -.0147700
0.6000000 -.0175200
0.7000000 -.0173100
0.8000000 -.0147400
0.9000000 -.0100100
0.9500000 -.0057300
1.0000000 -.0000200
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Polars for USA 27 mod. AIRFOIL (usa27m2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa27m2-il | 50,000 | 9 | 17.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 50,000 | 5 | 32.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27m2-il | 100,000 | 9 | 47.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 100,000 | 5 | 48.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27m2-il | 200,000 | 9 | 64.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 200,000 | 5 | 62.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27m2-il | 500,000 | 9 | 86.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 500,000 | 5 | 85 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27m2-il | 1,000,000 | 9 | 110 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 1,000,000 | 5 | 102.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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