Investigation of Flow Field in a Typical Hypersonic Wind Tunnel over a Standard Mode

In order to start designing a new hypersonic wind tunnel, it is important to have a pre-view about physical phenomena in a typical Hypersonic Wind Tunnel (HWT). In present research, it is tried to view phenomenologically the aerodynamics of flow in a typical HWT by Computational Fluid Dynamics (CFD). The considered HWT consists of a curved nozzle in nominal Mach number 12, free-jet type test section, a test model and a convergent-divergent diffuser. Aerodynamics of flow in the nozzle exit and test section, conical shock wave system in the diffuser and flow over a standard model (HB-2) are investigated. A method is introduced for numerical simulation of capturing the free shear layer in free-jet test section based on the vorticity distribution of flow. The aerodynamics behavior of HB-2 model is investigated in various Mach numbers and flow domains. The results make a better view of some aerodynamic phenomena in a free-jet type test section of wind tunnel that are rarely considered. This research is conducted towards the project of designing and manufacturing the industrial hypersonic wind tunnel for Qadr Aerodynamic research Center.

Investigation of Flow Field in a Typical Hypersonic Wind Tunnel over a Standard Mode Keywords:

Hypersonic , Standard Model , Wind tunnel , CFD