Airfoil database search
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.
(ah93k131-il) AH 93-K-131/15 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Althaus 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 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file | |
![]() | Peter 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 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Wortmann 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 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Wortmann 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%) | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | 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 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Gottingen 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 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | NASA/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%) | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | 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 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Boeing 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 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Eppler 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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