RG 14 10% AIRFOIL (rg1410-il)
RG 14 10% AIRFOIL - Rolf Girsberger RG 14 (10%) airfoil
| Details | Dat file | Parser | |
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(rg1410-il) RG 14 10% AIRFOIL Rolf Girsberger RG 14 (10%) airfoil Max thickness 10% at 31% chord. Max camber 1.6% at 36% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RG 14 10% AIRFOIL
30. 30.
0.0000000 0.0000000
0.0046500 0.0107200
0.0144700 0.0194000
0.0293800 0.0277800
0.0493100 0.0356000
0.0741200 0.0427100
0.1036300 0.0490300
0.1375600 0.0541900
0.1755900 0.0588600
0.2173000 0.0623300
0.2622700 0.0645600
0.3099800 0.0655700
0.3598900 0.0654100
0.4114400 0.0641200
0.4640100 0.0618300
0.5170100 0.0586100
0.5697900 0.0546500
0.6217500 0.0500900
0.6722700 0.0450500
0.7207300 0.0397200
0.7668900 0.0342000
0.8105700 0.0286100
0.8512100 0.0231200
0.8881100 0.0179300
0.9206300 0.0131500
0.9481700 0.0089300
0.9702600 0.0051900
0.9865400 0.0022200
0.9965900 0.0004900
1.0000000 0.0000000
0.0000000 0.0000000
0.0046500 -.0072600
0.0144700 -.0130200
0.0293800 -.0181900
0.0493100 -.0226900
0.0741200 -.0264300
0.1036300 -.0294400
0.1375600 -.0317100
0.1755900 -.0333100
0.2173000 -.0342500
0.2622700 -.0346100
0.3099800 -.0344300
0.3598900 -.0337500
0.4114400 -.0326500
0.4640100 -.0311900
0.5170100 -.0293800
0.5697900 -.0273000
0.6217500 -.0249400
0.6722700 -.0223300
0.7207300 -.0193100
0.7668900 -.0157500
0.8105700 -.0119800
0.8512100 -.0085300
0.8881100 -.0056200
0.9206300 -.0033400
0.9481700 -.0017100
0.9702600 -.0006200
0.9865400 -.0000600
0.9965900 0.0000500
1.0000000 0.0000000
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Polars for RG 14 10% AIRFOIL (rg1410-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg1410-il | 50,000 | 9 | 32.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1410-il | 50,000 | 5 | 33.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1410-il | 100,000 | 9 | 48.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1410-il | 100,000 | 5 | 46.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1410-il | 200,000 | 9 | 63.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1410-il | 200,000 | 5 | 58.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1410-il | 500,000 | 9 | 82.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1410-il | 500,000 | 5 | 71.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1410-il | 1,000,000 | 9 | 89.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1410-il | 1,000,000 | 5 | 85.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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