Intelligent Controller Design for a Blowdown Supersonic Wind Tunnel

Supersonic Blowdown Wind Tunnel Control Using LabVIEW

A computer-based, proportional-integral control system for supersonic blowdown wind tunnels was developed in a LabVIEW environment. The control algorithm is based on numerically integrating the differential equations used to model a supersonic blowdown wind tunnel in which the proportional and integral control terms were added and tuned in a simulation to determine their appropriate values. Val...

Pre-programmed Controller for a Supersonic Blowdown Tunnel

A Low Cost Numerical Simulation of a Supersonic Wind-tunnel Design

In the present paper, a supersonic wind-tunnel is designed to maintain a flow with Mach number of 3 in a 30cm×30cm test section. An in-house CFD code is developed using the Roe scheme to simulate flow-field and detect location of normal shock in the supersonic wind-tunnel. In the Roe scheme, flow conditions at inner and outer sides of cell faces are determined using an upwind biased algorithm. ...

Design of a PI controller with Anti-reset wind up for a Wind Tunnel

Wind tunnel is a test facility used to simulate the flight conditions. It allows us to make a reusable prototype and test it in the tunnel in low cost. Hypersonic wind tunnels operate at hypersonic speeds ie, with a mach number greater than 6. For doing experiments, it is necessary to maintain a constant pressure in the settling chamber of the tunnel so that we get the desired mach number and m...

Design Proposal for Three Two-Dimensional Wind Tunnel Nozzles for Supersonic Probe Calibration

Although newer techniques such as laser Doppler and hot-wire anemometry have emerged, aerodynamic probes remain the best tools for the analysis of flows in turbomachines. Based on the nature of how these probes accomplish this analysis, they must be calibrated in well known flows prior to use. This calibration takes place in wind tunnels with uniform, parallel flows at precise Mach numbers. The...