KSME International Journal

, Volume 15, Issue 12, pp 1816–1821 | Cite as

Transitional behavior of a supersonic flow in a two-dimensional diffuser

Special Issue in Flow Visualization


Two-dimensional blow-down type supersonic wind tunnel was designed and built to investigate the transient behavior of the startup of a supersonic flow from rest. The contour of the divergent part of the nozzle was determined by the MOC calculation. The converging part of the nozzle, upstream of the throat was contoured to make the flow profile uniform at the throat. The flow characteristics of the steady supersonic condition were visualized using the highspeed schlieren photography. The Mach number was evaluated from the oblique shock wave angle on a sharp wedge with half angle of 5 degree. The measured Mach number was 2.4 and was slightly less than the value predicted by the design calculation. The initial transient behavior of the nozzle was recorded by a high-speed digital video camera with schlieren technique. The measured transition time from standstill to a steady supersonic flow was estimated by analyzing the serial images. Typical transition time was approximately O.1sec.

Key Words

Supersonic Diffuser MOC Transition to Supersonic Flow Ejector 



Nozzle throat area


Mach number at nozzle exit


Air mass


Stagnation pressure in air tank


Gas constant


Stagnation temperature


Tank volume


Wedge angle


Specific heat ratio


Oblique shock angle


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Copyright information

© The Korean Society of Mechanical Engineers (KSME) 2001

Authors and Affiliations

  1. 1.Division of Aerospace Engineering Department of Mechanical Engineering Korea Advanced Institute of Science and TechnologyTaejonKorea

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