USA 26 AIRFOIL (usa26-il)
USA 26 AIRFOIL - USA-26 airfoil
| Details | Dat file | Parser | |
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(usa26-il) USA 26 AIRFOIL USA-26 airfoil Max thickness 9.8% at 19.9% chord. Max camber 4.3% at 39.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
USA 26 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0123000 0.0181400
0.0246800 0.0290700
0.0495100 0.0445400
0.0743800 0.0564200
0.0992800 0.0650900
0.1491500 0.0774400
0.1990500 0.0861900
0.2989900 0.0913900
0.3990300 0.0883900
0.4991100 0.0810900
0.5992100 0.0721900
0.6993400 0.0599900
0.7995099 0.0443900
0.8997200 0.0252000
0.9498500 0.0132500
1.0000000 0.0000000
0.0000000 0.0000000
0.0126400 -.0125600
0.0251600 -.0151200
0.0501700 -.0158500
0.0751700 -.0159700
0.1001800 -.0166000
0.1501700 -.0150500
0.2001300 -.0120000
0.3000500 -.0049000
0.4000200 -.0016000
0.5000500 -.0042000
0.6000900 -.0086000
0.7001000 -.0090000
0.8000900 -.0084000
0.9000700 -.0063000
0.9500400 -.0032500
1.0000000 0.0000000
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Polars for USA 26 AIRFOIL (usa26-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa26-il | 50,000 | 9 | 27.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa26-il | 50,000 | 5 | 35.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa26-il | 100,000 | 9 | 49.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa26-il | 100,000 | 5 | 52.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa26-il | 200,000 | 9 | 69.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa26-il | 200,000 | 5 | 69.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa26-il | 500,000 | 9 | 95.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa26-il | 500,000 | 5 | 92.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa26-il | 1,000,000 | 9 | 117.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa26-il | 1,000,000 | 5 | 108.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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