Experimental Investigation of the Effect of Boundary Layer Suction on the Performance of a Supersonic Air Intake

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Honaker, Zahra | 2014

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 46682 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Soltani, Mohammad Reza
Abstract:
An extensive wind tunnel tests were conducted on an axisymmetric supersonic inlet at free stream Mach numbers from 1.8 to 2.2, and at different values of mass flow rates. For each test, pressure distributions over the inlet spike was measured and the flow was visualized by means of the shadowgraph system and a high speed camera to obtain main performance characteristics of the inlet during its stable and unstable operations. As the Mach number is increased the pressure recovery is reduced, but maximum value of the mass flow rate is increased. The results of the stable operation of the inlet showed that, variations of the mass flow affects the surface pressure over the entire surface of the spike. Further, both pressure and Mach number at the end of the diffuser is changed. The results showed that the Mach number and the position of suction bleed have significant impact on the performance of the Intake
Keywords:
Waviness ; Boundary Layer Suction ; Performance ; Pressure Recovery ; Supersonic Intake ; Mass Flow Rate Scaling ; Axisymmetric Inlet Performance

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