Aircraft Model - High Wing
It has a wingspan of 266.25 mm, length of 217.5 mm with a NACA2415 wing profile.
AF1600H - Experiment
Aircraft Model - High Wing
The high wing model aircraft with NACA profile wings for use with the Large Subsonic Wind Tunnel (AF1600) is good for experiments with lift, drag and pitching moment of fixed wing aircraft.
Description
Essential Base Units
SUBSONIC WIND TUNNEL 600mm
AF1600S - Package
TecQuipment’s largest open-circuit subsonic wind tunnel, with a working section of 600 mm by 600 mm and 1250 mm long, is for the study of advanced aerodynamics theory and research. With the larger size comes greater visualisation and more accurate results, operating at meaningful Reynolds numbers.
Alternatives
Aircraft Model - Low Wing
AF1600G - Experiment
A low wing model aircraft with NACA2415 profile wings for use with TecQuipment's Large Subsonic Wind Tunnel (AF1600S)
Three-Dimensional Drag Models
AF1600J - Experiment
A set of different shape models with identical frontal area to allow students to compare the different coefficient of drag for each shape. Includes a dummy stem for tests to cancel out the drag due to each model’s support arm.
Set of Two NACA0012 Aerofoil models
AF1600D - Experiment
This set of two NACA0012 aerofoils allows students to compare the results from a full-width aerofoil with a half width aerofoil.
NACA2412 Aerofoil with Variable Flap
AF1600C - Experiment
A 150mm chord NACA2412 aerofoil with 590 span featuring a variable flap that adjusts +/- 90 degrees for use with the AF1600 Subsonic Wind Tunnel.
NACA0012 Aerofoil with Tappings
AF1600B - Experiment
A 150 mm chord NACA0012 aerofoil with 20 static pressure tappings.
CYLINDER MODEL
AF1600A - Experiment
A cylinder model that spans the full width of the working section of the AF1600S Subsonic Wind Tunnel.
Flat Plate Boundary Layer Model Roughened and Smooth
AF1600F - Experiment
A pair of boundary layer models with a mounting plate, also a pitot and a static probe for investigating boundary layer. One plate is roughened, the other smooth to allow comparisons on boundary layer growth.