Book Description

An investigation has been conducted in the NASA Langley 20-Foot Vertical Spin Tunnel to determine the static aerodynamic characteristics of a 1/25-scale model of the X-29A Forward Swept Wing airplane. The tests were conducted at a free-stream dynamic pressure of 3.6 lb/ft(exp 2), corresponding to a unit Reynolds number of 0.35x10(exp 6)/ ft, or 45x10(exp 5) based on a maximum fuselage forebody depth of 0.128ft. The purpose of this investigation was to assess the ability of various forebody devices to correct the aerodynamic parameters that are important in spin testing for Reynolds number effects. Low Reynolds number aerodynamic characteristics obtained for the X-29A during the present test were compared with high Reynolds number data obtained for this configuration in a previous test. The low Reynolds number tests were conducted first with the unmodified (baseline) model and then repeated with each of several forebody modifications installed.