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Article Dans Une Revue AIAA Journal Année : 2004

Numerical Investigation of Shock-Reflection Phenomena in Overexpanded Supersonic Jets

A N Kudryavtsev
  • Fonction : Auteur
M S Ivanov
  • Fonction : Auteur

Résumé

The transition from regular to Mach reflection in a supersonic planar jet operating under overexpanded conditions has been studied numerically. First, inviscid computations are performed by the solution of Euler equations. The results demonstrate that a hysteresis phenomenon is observed as the jet/ambient pressure ratio decreases and increases, causing a change in the angle of incidence of the nozzle-lip shock and, as a consequence, the transition from regular to Mach reflection and back. The angles of forward and backward transitions are close to the theoretical detachment and von Neumann criteria, respectively. Furthermore, turbulent computations (by the use of an improved two-equation model) are conducted to investigate the transition in a more realistic situation. The computations confirm the existence of the hysteresis and give the transition angles in very good agreement with both the theoretical criteria and the results of inviscid simulations. It appears that turbulence production is mainly concentrated in thin shear layers developing along the jet boundary, as well as the Mach stem slip streams, whereas the jet-core near field is characterized by a predominantly inviscid shock-cell structure. These observations justify the inviscid simulations when shock-wave reflection in the near field of supersonic jets is studied. Nomenclature c = speed of sound d = dilatatioñdilatatioñ E = total energy per unit mass h/2 = jet half-width k = turbulent kinetic energy L x , L y = sizes of computational domain M = Mach number P = static pressure P k = production of kinetic energy Pr = Prandtl number˜q number˜ number˜q = heat flux s = Mach stem height T = temperature t = time u i = velocity component in the x i direction α = shock-wave angle γ = ratio of specific heats ε = dissipation rate θ = flow deflection angle µ = viscosity ρ = density˜τ density˜ density˜τ i j = viscous and turbulent stresses Subscripts a = ambient conditions r = reservoir conditions t = turbulent values Superscripts ¯ = Reynolds-averaged quantities˜= quantities˜ quantities˜= Favre-averaged quantities = fluctuations of Favre-averaged quantities
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Dates et versions

hal-02082327 , version 1 (28-03-2019)

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  • HAL Id : hal-02082327 , version 1

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Abdellah Hadjadj, A N Kudryavtsev, M S Ivanov. Numerical Investigation of Shock-Reflection Phenomena in Overexpanded Supersonic Jets. AIAA Journal, 2004, 42. ⟨hal-02082327⟩
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