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Search the 1638 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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(ah93k131-il) AH 93-K-131/15

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AH 93-K-131/15Althaus AH 93-K-131/15 airfoil for use with flaps (K)
Max thickness 13.1% at 41.3% chord
Max camber 3.6% at 41.3% chord
Max Cl/Cd 25 at Re# 50,000
Source UIUC Airfoil Coordinates Database

(pw106-pw) PW106

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PW106Peter Wick. Modified PW51 with higher camber and therefore a higher clmax
Max thickness 8.9% at 27.5% chord
Max camber 2.1% at 27.5% chord
Max Cl/Cd 25 at Re# 50,000
Source RC Groups

(fx60177-il) FX 60-177 AIRFOIL

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FX 60-177 AIRFOILWortmann FX 60-177 airfoil
Max thickness 17.7% at 37.1% chord
Max camber 2.7% at 77.8% chord
Max Cl/Cd 25 at Re# 50,000
Source UIUC Airfoil Coordinates Database

(fx76120-il) WORTMANN FX 76-120

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WORTMANN FX 76-120Wortmann FX 76-120 symmetrical airfoil
Max thickness 12.1% at 27.9% chord
Max camber 0% at 0% chord
Max Cl/Cd 25 at Re# 50,000
Source UIUC Airfoil Coordinates Database

(s9032-il) S9032 (9%)

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S9032 (9%)Selig S9032 (9%) symmetrical horizontal stab airfoil used on the Blackhawk R/C sailplane
Max thickness 9% at 25% chord
Max camber 0% at 0% chord
Max Cl/Cd 25 at Re# 50,000
Source UIUC Airfoil Coordinates Database

(goe244-il) GOE 244 (MVA PR.4) AIRFOIL

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GOE 244 (MVA PR.4) AIRFOILGottingen 244 (MVA PR.4) airfoil
Max thickness 17.7% at 19.6% chord
Max camber 10% at 49.6% chord
Max Cl/Cd 25 at Re# 50,000
Source UIUC Airfoil Coordinates Database

(ls417-il) NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL

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NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOILNASA/Langley/Whitcomb LS(1)-0417 (GA(W)-1) general aviation airfoil
Max thickness 17% at 40% chord
Max camber 2.4% at 65% chord
Max Cl/Cd 25 at Re# 50,000
Source UIUC Airfoil Coordinates Database

(as5048-il) AS5048 (18%)

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AS5048 (18%)AS5048 airfoil Ashok Gopalarathnam/Selig 18% airfoil
Max thickness 18% at 38.3% chord
Max camber 0.8% at 77.8% chord
Max Cl/Cd 25 at Re# 50,000
Source UIUC Airfoil Coordinates Database

(kc135a-il) KC-135 BL52.44 AIRFOIL

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KC-135 BL52.44 AIRFOILBoeing KC-135 transonic airfoils
Max thickness 15.5% at 35% chord
Max camber 1.3% at 20% chord
Max Cl/Cd 24.9 at Re# 50,000
Source UIUC Airfoil Coordinates Database

(e637-il) EPPLER 637 AIRFOIL

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EPPLER 637 AIRFOILEppler E637 airfoil
Max thickness 12.1% at 27.6% chord
Max camber 3.6% at 23.6% chord
Max Cl/Cd 24.9 at Re# 50,000
Source UIUC Airfoil Coordinates Database
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