Aerodynamic design of axisymmetric hypersonic wind tunnel nozzles

Sivells, James C

doi:10.2514/6.1969-337

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2014

2023

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Cited by 5 publications

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“…유한한 값을 가지는 반지름 비 의 경우 sonic line은 곡면을 이루고 있으며 대칭축에서의 sonic point는 기하학적 노즐 목 지점으로부터 다음 식으로 표현된 거리에 위치해 있다 [1,2].…”

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Boundary Layer Correction of Hypersonic Wind-tunnel Nozzle Designed by the Methods of Characteristics

Kim¹,

Kim²,

Jeung³

et al. 2014

Journal of the Korean Society for Aeronautical & Space Scie

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A design procedure is established for hypersonic nozzles by using MOC(Method of Characteristics) and CFD. The inviscid nozzle contour is designed by MOC, then BLC(Boundary Layer Correction) is made by evaluating the boundary layer thickness from viscous CFD analysis. By comparing various definitions of the boundary layer thicknesses, it seems that the boundary layer thickness of 95% speed of the maximum value at the cross section satisfies best the design Mach number. Design procedure is as follow; MOC design, grid generation, inviscid analysis, viscous analysis, BLC and viscous analysis for confirmation and post-processing. All procedures are made automatically by using the batch processing.

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