Wind Tunnel Tests on A4, A4.1, and A4.2 2-D Airfoil Models in the Iar 5-Ft. WindTunnel: Boeing Commercial Airplane Company and Institute for Aerospace Research Collaborative Work Program

摘要

A wind tunnel project was undertaken to obtain aerodynamic data to investigatethe influence of the wind tunnel sidewall boundary layer effects by testing models with different aspect ratios. Wind tunnel investigations were performed on three airfoil models with the same airfoil section but with different chord lengths. The tests were performed over a Mach number range from 0.70 to 0.80 with the flow at a chord Reynolds number of 14 million. This project was undertaken as a collaborative wind tunnel program between Boeing Commercial Airplane Company and the Institute of Aerospace Research (Canada) to investigate the wall interference effects encountered during 2-D tests on transonic airfoils. The report includes some of the pertinent features of the test procedures, and the test parameters and variables used in the data processing procedures, to provide the information necessary to interpret the processed data. The analyses of the data are not included.