Turbulent flow in supersonic and hypersonic nozzles

Hu, Jiasen; Rizzi, Arthur

doi:10.2514/3.12861

Cited by 4 publications

(1 citation statement)

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“…Some researchers also addressed the effect of incoming turbulence on flow characteristics both experimentally and numerically [24,25]. Hu and Rizzi [26] investigated the transition to turbulence in supersonic and hypersonic nozzles using RANS and highlighted the effect of transition point near throat on the flowfield downstream of the nozzle. In addition to mimicking the boundary conditions correctly, geometry modeling also drives the accuracy of numerical simulations.…”

Section: Introductionmentioning

confidence: 99%

High-Order Accurate Numerical Simulation of Supersonic Flow Using RANS and LES Guided by Turbulence Anisotropy

Bhide

Abdallah

2022

Fluids

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This paper discusses accuracy improvements to Reynolds-Averaged Navier–Stokes (RANS) modeling of supersonic flow by assessing a wide range of factors for physics capture. Numerical simulations reveal complex flow behavior resulting from shock and expansion waves and so, a supersonic jet emanating from rectangular nozzle is considered. PIV based experimental data for the jet is available from literature and is used for validation purposes. Effect of various boundary conditions and turbulence modeling approaches is assessed qualitatively and quantitatively. Of particular interest are the inlet conditions considering the turbulence intensity and the effect of upstream air supply duct, the effect of nozzle wall surface roughness on nozzle internal flow and downstream, wall y+ sensitivity for boundary layer resolution and laminar to turbulent transition modeling. In addition to mesh sensitivity, domain dependency is conducted to evaluate the appropriate domain size to capture the kinetic energy dissipation downstream of the nozzle. To further improve the flow characteristics, accounting for the anisotropy of Reynolds stresses is also one of the focuses. Therefore, non-linear eddy viscosity-based two-equation model and Reynolds stress transport model are also investigated. Additionally, the results of baseline linear (Boussinesq) RANS are compared. Corresponding comparisons with high-fidelity LES are presented. Jet self-similar behavior resulting from all simulation fidelities is assessed and it appears that turbulent flow in LES becomes self-similar, but not in RANS. Finally, various factors such as the nozzle geometry and numerical modeling choices influencing the anisotropy in jet turbulence are discussed.

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Section: Introductionmentioning

confidence: 99%

High-Order Accurate Numerical Simulation of Supersonic Flow Using RANS and LES Guided by Turbulence Anisotropy

Bhide

Abdallah

2022

Fluids

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Aeroelastic Divergence of Stiffened Composite Multicell Wing Structures

Hwu

Tsai

2002

Journal of Aircraft

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When the wing is treated as a composite sandwich plate and it is assumed that the wing chordwise section is rigid, mathematical formulations for the stiffened composite multicell wing structures are provided, and associated governing equations for the aeroelastic divergence are also derived by a direct approach. When the matrix notation is used, the system of equations is written into an explicit and simple mathematical expression that can then be solved explicitly by using the technique of Laplace integral transform. In this modeling, the composite wing skins and stringers (including the spar anges) are simulated as the faces, whereas the spar webs and ribs are simulated as the core of the sandwiches. Because the wing cross section must have a streamline shape, unlike the usual uniform thickness modeling, it is more appropriate to simulate the wings as variable thickness sandwiches where the thickness is a function of the airfoil. Moreover, as is usual for assumptions for the sandwich plates, the effects of the transverse shear deformation are also considered. Because several special conditions have been studied in the literature, we rst compare our solutions with some existing solutions. To show the generality, several illustrative examples are given to consider the effects of spars, skins (including the ply orientation and stacking sequence), stringers, swept angles, aspect ratio, shape of airfoil, and the warping restraints on the divergence dynamic pressures and the lift loads redistribution.

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Radiative interactions in flows with chemical and vibrational nonequilibrium

Tiwari

Pidugu

2000

34th Thermophysics Conference

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Turbulent flow in supersonic and hypersonic nozzles

Cited by 4 publications

References 12 publications

High-Order Accurate Numerical Simulation of Supersonic Flow Using RANS and LES Guided by Turbulence Anisotropy

High-Order Accurate Numerical Simulation of Supersonic Flow Using RANS and LES Guided by Turbulence Anisotropy

Aeroelastic Divergence of Stiffened Composite Multicell Wing Structures

Radiative interactions in flows with chemical and vibrational nonequilibrium

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