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Airfoil database search (Symmetrical)

Search the 1636 airfoils available in the databases filtering by name, thickness and camber. Click on an airfoil image to display a larger preview picture. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers.

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(eh0009-il) EH 0.0/9.0

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EH 0.0/9.0John Yost EH 0.0/9.0 for tailless R/C aircraft
Max thickness 9% at 28.7% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(s9026-il) S9026 (9.5%)

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S9026 (9.5%)Selig S9026 (9.5%) symmetrical horizontal stab airfoil used on the Opus R/C sailplane
Max thickness 9.5% at 27.3% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(prandtl-d-tip-ns) Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag

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Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower DragNASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider tip airfoil
Max thickness 9.6% at 26.8% chord
Max camber 0% at 0% chord
Source NASA

(b540ols-il) BELL 540 AIRFOIL (MODIFIED NACA 0012)

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BELL 540 AIRFOIL (MODIFIED NACA 0012)Bell AH-1 rotor blade airfoil (operational loads survey)
Max thickness 9.7% at 22.1% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(raf27-il) RAF 27 AIRFOIL

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RAF 27 AIRFOILRAF-27 airfoil
Max thickness 9.8% at 30% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(bqm34-il) RYAN BQM-34 FIREBEE WING AIRFOIL

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RYAN BQM-34 FIREBEE WING AIRFOILRyan BQM-34 Firebee wing airfoil (NACA 63-014A W/NACA 0014 nose and thinned to .09899 to account for sweep)
Max thickness 9.9% at 32.5% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(sc20010-il) NASA SC(2)-0010 AIRFOIL

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NASA SC(2)-0010 AIRFOILNASA SC(2)-0010 airfoil (NASA TP-2969)
Max thickness 10% at 37% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(rae104-il) RAE 104 AIRFOIL

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RAE 104 AIRFOILRAE 104 airfoil
Max thickness 10% at 42% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(rae103-il) RAE 103 AIRFOIL

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RAE 103 AIRFOILRAE 103 airfoil
Max thickness 10% at 40% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database

(rae102-il) RAE 102 AIRFOIL

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RAE 102 AIRFOILRAE 102 airfoil
Max thickness 10% at 36% chord
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
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