Solution of thin layer Navier-Stokes equations for hypersonic flow of hydrogen-oxygen mixture over a conical body with a blunt ramp

1997 ◽  
Author(s):  
Gavriel Avital ◽  
J. Greenberg ◽  
Josef Rom ◽  
Gavriel Avital ◽  
J. Greenberg ◽  
...  
Keyword(s):  
Thin Layer ◽  
Hypersonic Flow ◽  
Stokes Equations ◽  
Navier Stokes ◽  
Oxygen Mixture ◽  
Conical Body ◽  
Navier Stokes Equations

Application of a Navier–Stokes Analysis to Flows Through Plane Cascades

1986 ◽  
Vol 108 (1) ◽  
pp. 103-111 ◽  
Author(s):  
O. Scha¨fer ◽  
H.-H. Fru¨hauf ◽  
B. Bauer ◽  
M. Guggolz
Keyword(s):  
Thin Layer ◽  
Stokes Equations ◽  
Density Ratio ◽  
Separated Flows ◽  
Stability And Convergence ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Fully Implicit ◽  
First Results ◽  
Viscous Solutions

A newly developed method is used to compute a variety of laminar/turbulent, attached/separated flows through plane turbine or compressor cascades. The thin-layer or full Navier–Stokes equations are solved in a 2-D or quasi-2-D/quasi-3-D form taking into account variable axial velocity density ratio/cascade aspect ratio. The turbulence is modeled by the Baldwin–Lomax algebraic two-layer eddy viscosity approach. Improved mesh generation and discretization techniques are introduced. A fully implicit formulation of the flow problem is developed which ensures high stability and convergence. Numerous quantitative comparisons of viscous solutions with experiments and other existing solutions are performed to validate the method. First results on the applicability of the thin-layer assumption are included.

Numerical analysis of exhaust jet secondary combustion in hypersonic flow field

2018 ◽  
Vol 32 (12n13) ◽  
pp. 1840045
Author(s):  
Tian-Peng Yang ◽  
Jiang-Feng Wang ◽  
Fa-Ming Zhao ◽  
Xiao-Feng Fan ◽  
Yu-Han Wang
Keyword(s):  
Flow Field ◽  
Hypersonic Flow ◽  
Flight Control ◽  
Stokes Equations ◽  
Field Structure ◽  
Control Surface ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Secondary Combustion ◽  
Exhaust Jet

The interaction effect between jet and control surface in supersonic and hypersonic flow is one of the key problems for advanced flight control system. The flow properties of exhaust jet secondary combustion in a hypersonic compression ramp flow field were studied numerically by solving the Navier–Stokes equations with multi-species and combustion reaction effects. The analysis was focused on the flow field structure and the force amplification factor under different jet conditions. Numerical results show that a series of different secondary combustion makes the flow field structure change regularly, and the temperature increases rapidly near the jet exit.

scholarly journals Diffusion and mixing effects in hot jet initiation and propagation of hydrogen detonations

2017 ◽  
Vol 836 ◽  
pp. 324-351 ◽  
Author(s):  
Xiaodong Cai ◽  
Ralf Deiterding ◽  
Jianhan Liang ◽  
Mingbo Sun ◽  
Yasser Mahmoudi
Keyword(s):  
Adaptive Mesh Refinement ◽  
Stokes Equations ◽  
Detonation Front ◽  
Navier Stokes ◽  
Oxygen Mixture ◽  
Small Scale ◽  
Helmholtz Instability ◽  
Navier Stokes Equations ◽  
Subsequent Formation ◽  
Jet Initiation

In the present work, the role of diffusion and mixing in hot jet initiation and detonation propagation in a supersonic combustible hydrogen–oxygen mixture is investigated in a two-dimensional channel. A second-order accurate finite volume method solver combined with an adaptive mesh refinement method is deployed for both the reactive Euler and Navier–Stokes equations in combination with a one-step and two-species reaction model. The results show that the small-scale vortices resulting from the Kelvin–Helmholtz instability enhance the reactant consumption in the inviscid result through the mixing. However, the suppression of the growth of the Kelvin–Helmholtz instability and the subsequent formation of small-scale vortices imposed by the diffusion in the viscous case can result in the reduction of the mixing rate, hence slowing the consumption of the reactant. After full initiation in the whole channel, the mixing becomes insufficient to facilitate the reactant consumption. This applies to both the inviscid and viscous cases and is due to the absence of the unburned reactant far away from the detonation front. Nonetheless, the stronger diffusion effect in the Navier–Stokes results can contribute more significantly to the reactant consumption closely behind the detonation front. However, further downstream the mixing is expected to be stronger, which eventually results in a stronger viscous detonation than the corresponding inviscid one. At high grid resolutions it is vital to correctly consider physical viscosity to suppress intrinsic instabilities in the detonation front, which can also result in the generation of less triple points even with a larger overdrive degree. Numerical viscosity was minimized to such an extent that inviscid results remained intrinsically unstable while asymptotically converged results were only obtained when the Navier–Stokes model was applied, indicating that solving the reactive Navier–Stokes equations is expected to give more correct descriptions of detonations.

Numerical Solution of the Azimuthal-Invariant Thin-Layer Navier-Stokes Equations

AIAA Journal ◽  
1980 ◽  
Vol 18 (12) ◽  
pp. 1411-1412 ◽  
Author(s):  
C. J. Nietubicz ◽  
T. H. Pulliam ◽  
J. L. Steger
Keyword(s):  
Thin Layer ◽  
Numerical Solution ◽  
Stokes Equations ◽  
Navier Stokes ◽  
Navier Stokes Equations
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