Wind Tunnel Testing on StartUnstart Characteristics of Finite Supersonic Biplane Wing

Abstract EN

This study describes the start/unstart characteristics of a finite and rectangular supersonic biplane wing.

Two wing models were tested in wind tunnels with aspect ratios of 0.75 (model A) and 2.5 (model B).

The models were composed of a Busemann biplane section.

The tests were carried out using supersonic and transonic wind tunnels over a Mach number range of 0.3≤M∞≤2.3 with angles of attack of 0°, 2°, and 4°.

The Schlieren system was used to observe the flow characteristics around the models.

The experimental results showed that these models had start/unstart characteristics that differed from those of the Busemann biplane (two dimensional) owing to three-dimensional effects.

Models A and B started at lower Mach numbers than the Busemann biplane.

The characteristics also varied with aspect ratio: model A (1.3

Model B was located in the double solution domain for the start/unstart characteristics at M∞=1.7, and model B was in either the start or unstart state at M∞=1.7.

Once the state was determined, either state was stable.