Fluid Dynamics

, Volume 10, Issue 6, pp 938–944 | Cite as

Experimental investigation of three-dimensional supersonic flow of a gas in the interference region of intersecting surfaces

  • V. S. Dem'yanenko


A contemporary high-speed aircraft represents a complex three-dimensional configuration, where supersonic gas flow is accompanied by numerous local flow interaction zones, in particular, near the intersection of different surfaces. Such a flow is characterized by three-dimensional systems of shock and expansion waves, and close to the surfaces one finds interaction of boundary layers and, above all, interaction of shock waves with the boundary layer. In general, the angular configurations are formed by intersection or contact of nonplanar surfaces with swept-back or blunted leading edges. This makes it practically impossible to obtain a rigorous theoretiical solution to the problem of gas flow over these surfaces, and presents considerable difficulty in an experimental investigation. It is therefore of interest to study the physical features of gas flow in corner configurations of very simple form [1–3]. The present paper examines the results of an experimental investigation of typical features of symmetric and asymmetric interaction of compressive, expansive, and mixed flows in the interference region of planar surfaces intersecting at an angle of less than 180‡.


Boundary Layer Shock Wave Supersonic Flow Expansion Wave Interaction Zone 
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Copyright information

© Plenum Publishing Corporation 1976

Authors and Affiliations

  • V. S. Dem'yanenko
    • 1
  1. 1.Novosibirsk

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