RAF 89 AIRFOIL (raf89-il)
RAF 89 AIRFOIL - RAF-89 airfoil
| Details | Dat file | Parser | |
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(raf89-il) RAF 89 AIRFOIL RAF-89 airfoil Max thickness 25% at 30% chord. Max camber 1.6% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAF 89 AIRFOIL
13. 13.
0.0000000 0.0000000
0.0250000 0.0523200
0.0500000 0.0730500
0.1000000 0.1003900
0.2000000 0.1294800
0.3000000 0.1393700
0.4000000 0.1375600
0.5000000 0.1275500
0.6000000 0.1091400
0.7000000 0.0840300
0.8000000 0.0565200
0.9000000 0.0285100
1.0000000 0.0000000
0.0000000 0.0000000
0.0250000 -.0484800
0.0500000 -.0663500
0.1000000 -.0878100
0.2000000 -.1074200
0.3000000 -.1106300
0.4000000 -.1054400
0.5000000 -.0947500
0.6000000 -.0767600
0.7000000 -.0582700
0.8000000 -.0382800
0.9000000 -.0192900
1.0000000 0.0000000
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Polars for RAF 89 AIRFOIL (raf89-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf89-il | 50,000 | 9 | 1.6 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 50,000 | 5 | 7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 100,000 | 9 | 18.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 100,000 | 5 | 27.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 200,000 | 9 | 45.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 200,000 | 5 | 36 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 500,000 | 9 | 50.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 500,000 | 5 | 39.7 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 1,000,000 | 9 | 56.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 1,000,000 | 5 | 45.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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