Journal of Selected Topics in Energy

 Supersonic wind tunnels are strong and useful tools for the detection of the flow physics around flying vehicles. In this work, a blowdown type supersonic wind tunnel with a Mach number of 3 was studied. The required air for the tunnel was supplied by a storage tank containing compressed air. The intended velocity in the test section of the wind tunnel is provided by the high pressure discharge of the air from the storage tank into the atomosphere. The nozzle's geometry has been designed based on the "characteristics" method. Embedding the injector in the wind tunnel provides the opportunity to launch the wind tunnel at lower compression ratios. Since the duration of the experimental data collection is limited in blowdown supersonic wind tunnel, proper design and exploitation of the injector in a way to allow tunnel launching at decreased compression ratios, provides significant influence on the saving the compressed air of the storage tank and increasing the experiment duration. It has been attempted in this work to study the effect of installation of the injector in wind tunnel through assessing the boundary layer and the flow physics inside the wind tunnel. The results show that the injected flow increases the energy level of the low energy boundary layer, so as the energy of the boundary layer in a placed ahead of the injector location is higher than a place before the injector location. This fact results in a decreased required compression ratio for tunnel launching. The physics of the formed flow was studied and physical phenomena such as boundary layer separations, bow shock, barrel shock and mach disk were reported around the injection site 

This study aims at investigating aerodynamic coefficients changes by applying a two-dimensional heat flux on the wing in transonic regime. The numerical and experimental researches have shown that heat transfer on the fuselage has a significant impact on reducing drag (force). The current study aims also at investigating the effects of the heat transfer on aerodynamic coefficients of wing section. Accordingly, the turbulent transonic flow was numerically simulated around RAE2822 transonic airfoil with two different methods of modeling turbulent flow, namely, k–ε two-equation method and Reynolds stress five-equation model (RSM) and the obtained results were compared with experimental results. After choosing RSM as an appropriate method, subsequent investigations have been carried out with it. By applying heat flux in certain parts of upper and lower airfoil, the flow around it, is modeled and aerodynamic coefficients are extracted for airfoil and investigated. Studies showed that heating below the airfoil surface leads to change of aerodynamic coefficients with increasing the lift to drag ratio which can reduce fuel consumption and increase endurance of aircraft.