RG 15A 2.5/13.0 AIRFOIL (rg15a213-il)
RG 15A 2.5/13.0 AIRFOIL - Rolf Girsberger RG 15A 2.5/13.0 airfoil
| Details | Dat file | Parser | |
|
(rg15a213-il) RG 15A 2.5/13.0 AIRFOIL Rolf Girsberger RG 15A 2.5/13.0 airfoil Max thickness 13% at 30.2% chord. Max camber 2.5% at 39.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RG 15A 2.5/13.0 AIRFOIL
32. 32.
0.0000000 0.0000000
0.0015600 0.0084500
0.0075300 0.0182700
0.0187900 0.0286800
0.0342800 0.0390100
0.0544000 0.0489200
0.0787800 0.0581400
0.1073000 0.0664600
0.1396900 0.0736700
0.1756900 0.0796400
0.2149700 0.0842600
0.2571700 0.0874600
0.3019100 0.0892200
0.3487700 0.0895600
0.3973000 0.0885300
0.4470700 0.0862100
0.4974200 0.0827100
0.5479500 0.0781500
0.5981300 0.0726700
0.6476100 0.0664400
0.6958200 0.0596600
0.7421800 0.0525000
0.7861300 0.0451800
0.8271700 0.0378700
0.8648100 0.0307700
0.8985800 0.0240500
0.9280500 0.0178800
0.9528000 0.0123000
0.9725900 0.0073000
0.9873500 0.0032400
0.9967300 0.0007700
1.0000000 0.0000000
0.0000000 0.0000000
0.0045400 -.0074100
0.0145500 -.0138900
0.0265100 -.0193400
0.0433200 -.0245500
0.0635800 -.0289600
0.0887500 -.0327300
0.1157700 -.0357400
0.1472400 -.0380600
0.1820600 -.0396700
0.2200100 -.0406300
0.2608100 -.0409600
0.3041900 -.0407100
0.3497900 -.0398900
0.3972200 -.0385400
0.4460700 -.0366500
0.4958900 -.0342200
0.5463500 -.0311100
0.5967900 -.0270200
0.6461900 -.0222300
0.6940800 -.0173100
0.7401600 -.0126600
0.7839400 -.0085000
0.8249500 -.0050200
0.8626900 -.0023000
0.8966900 -.0003900
0.9264700 0.0007600
0.9515400 0.0012500
0.9717400 0.0012200
0.9869800 0.0008400
0.9966600 0.0002800
1.0000000 0.0000000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for RG 15A 2.5/13.0 AIRFOIL (rg15a213-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rg15a213-il | 50,000 | 9 | 29.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a213-il | 50,000 | 5 | 34.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a213-il | 100,000 | 9 | 50.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a213-il | 100,000 | 5 | 51.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a213-il | 200,000 | 9 | 69.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a213-il | 200,000 | 5 | 66.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a213-il | 500,000 | 9 | 93.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a213-il | 500,000 | 5 | 84.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a213-il | 1,000,000 | 9 | 108.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a213-il | 1,000,000 | 5 | 96.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||