USA 5 AIRFOIL (usa5-il)
USA 5 AIRFOIL - USA-5 airfoil
| Details | Dat file | Parser | |
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(usa5-il) USA 5 AIRFOIL USA-5 airfoil Max thickness 6.4% at 30% chord. Max camber 4.5% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
USA 5 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0137300
0.0250000 0.0231600
0.0500000 0.0370100
0.0750000 0.0469700
0.1000000 0.0551300
0.1500000 0.0650400
0.2000000 0.0725600
0.3000000 0.0771900
0.4000000 0.0753200
0.5000000 0.0704500
0.6000000 0.0616800
0.7000000 0.0505100
0.8000000 0.0365400
0.9000000 0.0195700
0.9500000 0.0098800
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0055700
0.0250000 -.0069400
0.0500000 -.0068800
0.0750000 -.0046300
0.1000000 -.0010700
0.1500000 0.0045400
0.2000000 0.0090600
0.3000000 0.0133900
0.4000000 0.0153200
0.5000000 0.0132500
0.6000000 0.0102800
0.7000000 0.0059100
0.8000000 0.0022400
0.9000000 -.0012300
0.9500000 -.0031200
1.0000000 0.0000000
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Polars for USA 5 AIRFOIL (usa5-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa5-il | 50,000 | 9 | 38.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa5-il | 50,000 | 5 | 40.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa5-il | 100,000 | 9 | 55.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa5-il | 100,000 | 5 | 56.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa5-il | 200,000 | 9 | 72.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa5-il | 200,000 | 5 | 71 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa5-il | 500,000 | 9 | 95 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa5-il | 500,000 | 5 | 91.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa5-il | 1,000,000 | 9 | 112.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa5-il | 1,000,000 | 5 | 99.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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