NACA 0012 AEROFOIL MODEL WITH PRESSURE TAPPINGS

A 150 mm chord 300 mm span aerofoil with pressure tappings for use with the Subsonic Wind Tunnel.

The aerofoil has 20 static pressure tappings along its chord on the upper and lower surfaces. They each connect to tubes that pass through the aerofoil and then out to clear, numbered, flexible tubes. Students can connect the tubes to other optional pressure-measurement instruments. Learn about NACA 0012 AEROFOIL MODEL WITH PRESSURE TAPPINGS specifications for optimal educational outcomes.. They can then measure the pressure distribution around the aerofoil, from which they can find the lift. Using a Pitot tube, students can traverse the aerofoil wake to find the downstream pressure distribution and find the drag on the aerofoil. Learn about NACA 0012 AEROFOIL MODEL WITH PRESSURE TAPPINGS exporters for optimal educational outcomes.. Students can compare these values of lift and drag with direct measurements found from a balance. Varying the angle of attack of the aerofoil with respect to the air stream allows students to find the changes to the pressure distribution. Learn about Pressure Distribution NACA 0012 AEROFOIL MODEL WITH PRESSURE TAPPINGS for optimal educational outcomes.. It also allows investigations into the critical conditions at stall.