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Installation, Simulation and Calibration of SARL Low-Speed Wind Tunnel

Zavaree, Sam | 2022

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 55294 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Farahani, Mohammad
  7. Abstract:
  8. As an essential laboratory instrument in aerospace engineering, wind tunnels need to be calibrated. Therefore, this thesis takes into account the calibration of the subsonic wind tunnel at the Sharif University of Technology, with the test section dimensions of 90 × 42 × 30 cm3. It is necessary to accurately and correctly determine the effective parameters for the wind tunnel results to be reliable. A pitot-static tube, a standard wing, pressure sensors, a force balance, a turbulence sphere, rake, yawhead, a digital level, a protractor, and a data acquisition system were used for this experiment. For calibration, variables including flow uniformity, flow Angularity, turbulence intensity, standard wing force coefficients, speed and total pressure inside the test section, the longitudinal static pressure of the wind tunnel wall, and wing surface have been measured. In verifying the results of the wind tunnel, a machine learning algorithm and numerical solution prediction results have been used. The outcomes demonstrated that the flow uniformity in a 20 × 10 cm2 area at a depth of approximately 16 cm from the test section center is acceptable for producing suitable results. The flow angle was measured by two methods and the maximum was -0.4 ± 0.1 degrees for longitudinal and -0.3 ± 0.1 degrees for lateral. The turbulence intensity was reported to be about 0.5%, which is acceptable for the mentioned wind tunnel. Additionally, the dynamic pressure drop parameter was in the permitted range. Finally, the tunnel surface's static pressure and a standard wing surface confirmed the flow quality
  9. Keywords:
  10. Wind Tunnel Calibration ; Machine Learning ; Flow Uniformity ; Pressure Sensor ; Flow Angularity ; Subsonic Wind Tunnel

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