(rae102-il) RAE 102 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| RAE 102 airfoil Max thickness 10% at 36% chord Max camber 0% at 0% chord Max Cl/Cd 28.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(raf27-il) RAF 27 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| RAF-27 airfoil Max thickness 9.8% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 28.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(hq010-il) HQ 0/10 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| Quabeck HQ 0/10 R/C sailplane airfoil Max thickness 10% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 28 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(rae101-il) RAE 101 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| RAE 101 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 27.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(rae103-il) RAE 103 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| RAE 103 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 27.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(fx79l100-il) FX 79-L-100 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| Wortmann FX 79-L-100 symmetrical airfoil Max thickness 10.1% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 27.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(raf27-il) RAF 27 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| RAF-27 airfoil Max thickness 9.8% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 27.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(rae101-il) RAE 101 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| RAE 101 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 27.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(rae102-il) RAE 102 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| RAE 102 airfoil Max thickness 10% at 36% chord Max camber 0% at 0% chord Max Cl/Cd 27.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(n63010a-il) NACA 63A010 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| NACA 63-010A airfoil Max thickness 10% at 35% chord Max camber 0% at 0% chord Max Cl/Cd 27.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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