Integrated Numerical Simulation Research of High-speed Section in Transonic Wind Tunnel

Abstract

For civil aviation aircraft with high subsonic economic cruising and fighter with high maneuverability at transonic speed, their demand for high-performance transonic wind tunnels is becoming more and more urgent, and integrated numerical simulation research of high-speed section in transonic wind tunnel which has certain reference significance for the design of transonic wind tunnel is analyzed. Through an example of an asymmetric flat plate diffuser, the feasibility of the calculation method is initially verified. At the same time, the convergence and evaluation methods for the high-speed section of the transonic wind tunnel, different initial conditions, and the expansion angle of the groove wall are studied. The results indicate that the changing of the Mach number of monitoring points in model section can be the numerical convergence criteria. The influence on velocity distribution at model section and streamline in slot with different initial conditions is negligible. Moreover, the slotted wall divergence angle 0.3° acquires more uniform flow fields than divergence angle 0.0°.

Keywords

• transonic wind tunnel
• wind tunnel design
• slotted wall divergence angle
• test section
• trip3.0
• convergence criterion