USA 27 AIRFOIL (usa27-il)
USA 27 AIRFOIL - USA-27 airfoil
| Details | Dat file | Parser | |
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(usa27-il) USA 27 AIRFOIL USA-27 airfoil Max thickness 11.1% at 30% chord. Max camber 5.1% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
USA 27 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0204400
0.0250000 0.0325800
0.0500000 0.0518600
0.0750000 0.0651400
0.1000000 0.0754200
0.1500000 0.0889800
0.2000000 0.0985400
0.3000000 0.1056600
0.4000000 0.1037800
0.5000000 0.0969000
0.6000000 0.0850200
0.7000000 0.0711400
0.8000000 0.0522600
0.9000000 0.0293800
0.9500000 0.0159400
1.0000000 0.0002000
0.0000000 0.0000000
0.0125000 -.0125600
0.0250000 -.0138200
0.0500000 -.0152400
0.0750000 -.0158600
0.1000000 -.0163800
0.1500000 -.0150200
0.2000000 -.0118600
0.3000000 -.0050400
0.4000000 -.0018200
0.5000000 -.0046000
0.6000000 -.0081800
0.7000000 -.0092600
0.8000000 -.0086400
0.9000000 -.0064200
0.9500000 -.0037600
1.0000000 0.0000000
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Polars for USA 27 AIRFOIL (usa27-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa27-il | 50,000 | 9 | 20.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 50,000 | 5 | 35.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 100,000 | 9 | 50.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 100,000 | 5 | 52.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 200,000 | 9 | 69.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 200,000 | 5 | 69 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 500,000 | 9 | 95.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 500,000 | 5 | 92 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 1,000,000 | 9 | 117.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 1,000,000 | 5 | 110.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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