Design Proposal for Three Two-Dimensional Wind Tunnel Nozzles for Supersonic Probe Calibration
نویسنده
چکیده
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 existing probe calibration wind tunnel at the division of Heat and Power Technology (HPT) at KTH has an operating range of Mach 0.1 to 0.95. This report seeks to provide guidance for the production of three new nozzles for this wind tunnel to raise the calibration range to Mach 1.2. The three nozzles will be designed to operate at Mach 1.0, 1.1, and 1.2 to allow for a range of probe calibration values. This report will also include a cursory investigation into the loading effect of the supersonic flow on the probes to be calibrated. Royal Institute of Technology Division of Heat & Power Technology Duke University Pratt School of Engineering
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