RAF 26 AIRFOIL (raf26-il)
RAF 26 AIRFOIL - RAF-26 airfoil
| Details | Dat file | Parser | |
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(raf26-il) RAF 26 AIRFOIL RAF-26 airfoil Max thickness 6.6% at 29.9% chord. Max camber 2.1% at 49.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAF 26 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0122800 0.0107500
0.0246700 0.0162100
0.0495300 0.0231200
0.0744400 0.0275300
0.0993400 0.0324400
0.1492000 0.0391600
0.1991000 0.0440800
0.2989600 0.0507300
0.3989500 0.0518200
0.4989500 0.0510300
0.5990600 0.0458800
0.6992100 0.0383300
0.7994200 0.0282900
0.8996601 0.0166400
0.9497899 0.0104700
1.0000000 0.0000000
0.0000000 0.0000000
0.0126500 -.0075400
0.0252100 -.0104800
0.0502800 -.0137700
0.0753200 -.0154600
0.1003400 -.0164400
0.1503600 -.0174200
0.2003500 -.0172900
0.3003200 -.0154400
0.4002400 -.0118000
0.5001700 -.0082500
0.6001000 -.0051000
0.7000500 -.0025500
0.8000200 -.0010000
0.9000100 -.0006500
0.9500300 -.0012200
1.0000000 0.0000000
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Polars for RAF 26 AIRFOIL (raf26-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf26-il | 50,000 | 9 | 34 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 50,000 | 5 | 37.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf26-il | 100,000 | 9 | 53.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 100,000 | 5 | 51.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf26-il | 200,000 | 9 | 71.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 200,000 | 5 | 62.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf26-il | 500,000 | 9 | 88.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 500,000 | 5 | 69.8 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf26-il | 1,000,000 | 9 | 94.1 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 1,000,000 | 5 | 76.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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