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Experimental Investigation of Pressure Distribution on the Surface of a Supercritical Airfoil in Transonic Regime

Talebi, Masoud | 2014

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 46605 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Soltani, Mohammad Reza
  7. Abstract:
  8. Transonic flow study is important due to its vast applications. Supercritical airfoils are designed for transonic flow to postpone drag divergence and reduce the strength of shock. This type of airfoils are chiefly used in modern commercial airplanes because of their low drag in transonic regime and, as a result, reduction in their fuel consumption. Using supercritical airfoils needs accurate investigation of flow field due to several influential factors such as specific geometry, nonlinear nature of flow phenomena, and compressibility effects. However, the availability of experimental and numerical data for supercritical airfoils is less than that of the conventional ones. Thus, experimental tests are essential for understanding the flow field around supercritical airfoils.
    In this thesis aerodynamic characteristics of a supercritical airfoil in transonic regime was investigated. For this purpose, a two-dimensional model was constructed and its surface pressure was measured in a transonic wind tunnel to study the effects of different parameters such as surface roughness, Mach number and angle of attack. The results of this thesis can be used for Aircraft designing purposes. Furthermore, the data can be employed for validation of numerical codes
  9. Keywords:
  10. Transonic Flow ; Pressure Distribution ; Supercritical Airfoil ; Experimental Evaluation

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