Analytical Prediction of the Turbulent Base Pressure in Supersonic Axisymmetric Flow Including the Effect of Initial Flow Direction PDF Download
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Author: T. J. Mueller
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 113
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Book Description
Author: T. J. Mueller
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 113
Get Book Here
Book Description
Author: T. J. Mueller
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 9
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Book Description
Author: C. E. Peters
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 80
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Book Description
An analytical model for planar and axisymmetric, supersonic, turbulent, near-wake flows is presented. The viscous region behind the blunt base is described by the integral form of the boundary-layer equations, and the inviscid outer-flow region, including the remnant of the initial turbulent boundary layer, is computed with the rotational method of characteristics. The solution of the two regions is fully coupled. The saddle-point singularity, similar to the Crocco-Lees critical point, occurs downstream of the rear stagnation point. The base pressure is obtained by iteration of the initial conditions until the flow-field solution will pass through the singularity. Base bleed of a gas different from the outer-stream gas is included in the formulation, and provision is made to treat equilibrium chemical reactions in the viscous wake. However, an unresolved problem has been encountered in the solution of the species conservation equations. Therefore, results for only single gas flows are presented. The analytical model is shown to adequately predict the effect of free-stream Mach number and initial boundary layer on the planar base pressure. In addition, the planar flow-field structure is well predicted. Axisymmetric base pressure and flow-field structure are reasonably well predicted for free-stream Mach numbers greater than 2.0, but the turbulent transport model used yields only fair results for Mach numbers less than 1.7. The effect of base bleed on the axisymmetric base pressure is well predicted. (Author).
Author: C. E. Peters
Publisher:
ISBN:
Category :
Languages : en
Pages : 78
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Book Description
An analytical model for planar and axisymmetric, supersonic, turbulent, near-wake flows is presented. The viscous region behind the blunt base is described by the integral form of the boundary-layer equations, and the inviscid outer-flow region, including the remnant of the initial turbulent boundary layer, is computed with the rotational method of characteristics. The solution of the two regions is fully coupled. The saddle-point singularity, similar to the Crocco-Lees critical point, occurs downstream of the rear stagnation point. The base pressure is obtained by iteration of the initial conditions until the flow-field solution will pass through the singularity. Base bleed of a gas different from the outer-stream gas is included in the formulation, and provision is made to treat equilibrium chemical reactions in the viscous wake. However, an unresolved problem has been encountered in the solution of the species conservation equations. Therefore, results for only single gas flows are presented. The analytical model is shown to adequately predict the effect of free-stream Mach number and initial boundary layer on the planar base pressure. In addition, the planar flow-field structure is well predicted. Axisymmetric base pressure and flow-field structure are reasonably well predicted for free-stream Mach numbers greater than 2.0, but the turbulent transport model used yields only fair results for Mach numbers less than 1.7. The effect of base bleed on the axisymmetric base pressure is well predicted. (Author).
Author: T. J. Mueller
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 138
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Book Description
Author: Alexander J. Smits
Publisher: Springer Science & Business Media
ISBN: 0387263055
Category : Science
Languages : en
Pages : 418
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Book Description
A good understanding of turbulent compressible flows is essential to the design and operation of high-speed vehicles. Such flows occur, for example, in the external flow over the surfaces of supersonic aircraft, and in the internal flow through the engines. Our ability to predict the aerodynamic lift, drag, propulsion and maneuverability of high-speed vehicles is crucially dependent on our knowledge of turbulent shear layers, and our understanding of their behavior in the presence of shock waves and regions of changing pressure. Turbulent Shear Layers in Supersonic Flow provides a comprehensive introduction to the field, and helps provide a basis for future work in this area. Wherever possible we use the available experimental work, and the results from numerical simulations to illustrate and develop a physical understanding of turbulent compressible flows.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 156
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 466
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1572
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Book Description
Author: John Laszlo Papp
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
The successful application of CFD and turbulence modeling methods to an aerospike nozzle system first involves the successful simulation of its key flow components. This report addresses the task using the Chien low-Re k-? and the Yakhot et al. high-Re RNG k-? turbulence models. An improved implicit axis of symmetry boundary condition is also developed to increase stability and lower artificial dissipation. Grid adaptation through the SAGE post-processing package is used throughout the study. The RNG model, after low-Re modifications, and the Chien low-Rek-? model are applied to the supersonic axisymmetric base flow problem. Both models predict a peak recirculation velocity almost twice as large as experiment. The RNG model predicts a flatter base pressure and lower recirculation velocity more consistent with experimental data using less grid points than a comparable Chien model solution. The turbulent quantities predicted by both models are typical of other numerical results and generally under predict peak values obtained in experiment suggesting that too little turbulent eddy viscosity is produced. After several test cases, the full 3-D aerospike nozzle is simulated using both the Chien and modified RNG low-Re models. The Chien model outperforms the RNG model in all circumstances. The surface pressure predicted by the Chien model along the nozzle center-plane is very near experiment while mid-plane results are not as close but useful for design purposes. The lack of a thick boundary layer along the nozzle surface in RNG simulations is the cause of poor surface pressure comparisons. Although initial base flow comparisons between the model predictions and experiment are poor, the profiles are relatively flat. To accelerate the progress to a steady-state solution, a process involving the artificial lowering of the base pressure and subsequent iteration to a new steady state is undertaken. After several of these steps, the resulting steady-state base pressure is very near experimental values. The effect of a slight geometry change on the flow characteristics is also examined through different thruster nozzle faceplate designs. The result of the slight modification is a tremendous reduction in surface pressure and temperature caused by recirculation at the thruster nozzle exit without adverse nozzle performance losses.
