Supersonic interference flow along the corner of intersecting wedges

Andrew F. Charwat, L. G. Redekopp

ResearchPublished 1966

An experimental investigation of the inviscid supersonic flow field in a corner formed by two intersecting wedges. Measurements of the distribution of the surface pressure and of the wave structure of the flow field in the corner region are obtained for a symmetrical corner configuration in the Mach number range between 2.5 and 4, and for an asymmetrical configuration at one Mach number as a function of the incidence angle of one wedge. A clearly identifiable shock structure divides the interference field into four zones. The total extent of the disturbance near the surfaces of the model is approximately twice the extent indicated by small perturbation analyses. The highest pressure rise occurs in the inner zone near the corner. The inviscid flow field shows strong cross-stream pressure and entropy gradients both at the corner itself and away from it. 59 pp. Refs.

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  • Copyright: RAND Corporation
  • Availability: Available
  • Year: 1966
  • Print Format: Paperback
  • Paperback Price: $23.00
  • Document Number: RM-4863-PR

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RAND Style Manual
Charwat, Andrew F. and L. G. Redekopp, Supersonic interference flow along the corner of intersecting wedges, RAND Corporation, RM-4863-PR, 1966. As of September 16, 2024: https://www.rand.org/pubs/research_memoranda/RM4863.html
Chicago Manual of Style
Charwat, Andrew F. and L. G. Redekopp, Supersonic interference flow along the corner of intersecting wedges. Santa Monica, CA: RAND Corporation, 1966. https://www.rand.org/pubs/research_memoranda/RM4863.html. Also available in print form.
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