Flow Field Calibration of a In-house Designed Direct Connected-pipe Wind Tunnel

Abstract

This thesis aims to calibrate the In-house designed direct connected-pipe wind tunnel which is composed of settling chamber nozzle and test section of 49 square centimeters This study uses two different shape of pitot tubes to measure the pressure and using flow visualization to obtain various flow field conditions Since the blunt object in the supersonic airflow will produce a bow shock at its front to affect the measured pressure so this thesis study uses the total pressure after the shock wave measured by the pitot tube and the static pressure at the wall surface to calculate the Mach number L-type pitot tube measures the uniformity of the flow field cross-section in the wind tunnel and analyze the Mach number distribution of the measured points from the results that the average Mach number in the cross-sectional measurement range is 1 90 The C-type pitot tube is used to measure the flow angle It is considered that the air flow is affected by the Mach wave The visualization of the flow field uses the Schlieren method to observe the shock wave distribution and boundary layer thickness The experimental analysis results show that the oblique shock wave in the test section is mainly the Mach wave generated by the nozzle and it has not yet been seen obviously interacted with the boundary layer Therefore it is believed that the distribution of the flow field in the Direct Connected-pipe wind tunnel is mainly affected by the Mach wave in the flow field

Date of Award	2020
Original language	English
Supervisor	Hsiao-Feng Yuan (Supervisor)