RAF 25 AIRFOIL (raf25-il)
RAF 25 AIRFOIL - RAF-25 airfoil
| Details | Dat file | Parser | |
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(raf25-il) RAF 25 AIRFOIL RAF-25 airfoil Max thickness 6.5% at 29.9% chord. Max camber 1% at 49.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAF 25 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0121700 0.0096200
0.0245200 0.0138500
0.0493400 0.0191100
0.0741700 0.0239700
0.0990500 0.0274400
0.1488600 0.0327700
0.1987200 0.0369000
0.2985100 0.0409800
0.3985600 0.0416300
0.4986400 0.0393000
0.5987900 0.0347800
0.6990300 0.0280600
0.7993200 0.0197400
0.8996200 0.0108200
0.9497899 0.0061600
1.0000000 0.0000000
0.0000000 0.0000000
0.0128200 -.0091600
0.0254300 -.0123200
0.0505600 -.0162500
0.0756500 -.0187700
0.1007200 -.0207100
0.1507900 -.0227700
0.2008300 -.0240300
0.3008200 -.0237600
0.4007600 -.0218900
0.5006400 -.0184300
0.6005100 -.0145600
0.7003700 -.0107000
0.8002500 -.0072300
0.9001400 -.0039700
0.9500800 -.0024300
1.0000000 0.0000000
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Polars for RAF 25 AIRFOIL (raf25-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf25-il | 50,000 | 9 | 28.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 50,000 | 5 | 30.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 100,000 | 9 | 43.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 100,000 | 5 | 40.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 200,000 | 9 | 56.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 200,000 | 5 | 47.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 500,000 | 9 | 68.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 500,000 | 5 | 55.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 1,000,000 | 9 | 72.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 1,000,000 | 5 | 68.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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