Current Search: Chow, Wen L. (x)
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- Title
- A numerical technique for multiple shock capturing in steady, quasi one-dimensional flows.
- Creator
- Brigandi, Joseph., Florida Atlantic University, Chow, Wen L.
- Abstract/Description
-
A numerical technique is given to capture multiple shocks in steady, quasi one-dimensional flows by solving the Euler equations from a sequence of implicit/explicit solutions for the Riemann variables. A supersonic wind tunnel with a variable area diffuser is analyzed with the results compared to exact solutions. Examples are given with both one and two standing shocks. The technique given is an extension of Moretti's scheme for a single discontinuity in a De Laval nozzle. It is shown that...
Show moreA numerical technique is given to capture multiple shocks in steady, quasi one-dimensional flows by solving the Euler equations from a sequence of implicit/explicit solutions for the Riemann variables. A supersonic wind tunnel with a variable area diffuser is analyzed with the results compared to exact solutions. Examples are given with both one and two standing shocks. The technique given is an extension of Moretti's scheme for a single discontinuity in a De Laval nozzle. It is shown that this efficient technique is easily adaptable and is equally accurate for multiple discontinuities as it is for a single discontinuity.
Show less - Date Issued
- 1990
- PURL
- http://purl.flvc.org/fcla/dt/14673
- Subject Headings
- Fluid dynamics, Compressibility--Computer programs, Shock waves--Computer programs
- Format
- Document (PDF)
- Title
- Base pressure resulting from sudden expansion in cross-sectional area from a conical converging nozzle.
- Creator
- Hwang, Chi-bok., Florida Atlantic University, Chow, Wen L., College of Engineering and Computer Science, Department of Ocean and Mechanical Engineering
- Abstract/Description
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This research concerns with the determination of the base pressure related to the conical convergent nozzle flow when a sudden enlargement in cross-sectional area occurs. It is recognized at the outset that the problem belongs to the category of strong interaction where inviscid and viscous flows must be considered together before a solution can be established. The viscous flow analyses based on the integral formulations are guided more or less by the boundary layer concept. The inviscid flow...
Show moreThis research concerns with the determination of the base pressure related to the conical convergent nozzle flow when a sudden enlargement in cross-sectional area occurs. It is recognized at the outset that the problem belongs to the category of strong interaction where inviscid and viscous flows must be considered together before a solution can be established. The viscous flow analyses based on the integral formulations are guided more or less by the boundary layer concept. The inviscid flow field is established from the hodograph transformation, and the method of characteristics. Again the point of reattachment behaves as a saddle point singularity for the system of equations describing the viscous flow recompression process. After the point of reattachment is approached, an overall momentum balance is applied so that the base pressure and the location where recompression starts, may be determined. Experimental studies with specific conical angles and area ratios are also conducted in the laboratory. The results obtained from the theoretical analysis agreed well with the experimental data produced in the laboratory and the data available elsewhere. These evidences lead to the conclusion that the method developed in this investigation is effective in dealing with problems of this type.
Show less - Date Issued
- 1991
- PURL
- http://purl.flvc.org/fcla/dt/12280
- Subject Headings
- Base flow (Aerodynamics), Viscous flow, Aerodynamics, Supersonic, Pressure vessels
- Format
- Document (PDF)
- Title
- A general pressure based Navier-Stokes solver in arbitrary configurations.
- Creator
- Ke, Zhao Ping., Florida Atlantic University, Chow, Wen L., College of Engineering and Computer Science, Department of Ocean and Mechanical Engineering
- Abstract/Description
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A pressure-based computer program for a general Navier-Stokes equations has been developed. Body-fitted coordinate system is employed to handle flows with complex geometry. Non-staggered grid is used while the pressure oscillation is eliminated by a special pressure interpolation scheme. The hybrid algorithm is adopted to discretize the equations and the finite-difference equations are solved by TDMA, while the whole solution is obtained through an under-relaxed iterative process. The...
Show moreA pressure-based computer program for a general Navier-Stokes equations has been developed. Body-fitted coordinate system is employed to handle flows with complex geometry. Non-staggered grid is used while the pressure oscillation is eliminated by a special pressure interpolation scheme. The hybrid algorithm is adopted to discretize the equations and the finite-difference equations are solved by TDMA, while the whole solution is obtained through an under-relaxed iterative process. The pressure field is evaluated using the compressible from of the SIMPLE algorithm., To test the accuracy and efficiency of the computer program, problems of incompressible and compressible flows are calculated. As examples of inviscid compressible flow problems, flows over a bump with 10% and 4% thickness are computed with the incoming Mach numbers of M[infinity] = 0.5 (subsonic flow), M[infinity] = 0.675 (transonic flow and M[infinity] = 1.65 (supersonic flow). One laminar subsonic flow over a bump with 5% thickness at M[infinity] = 0.5 is also calculated with the consideration of the full energy equation. With the help of the k-epsilon model incorporating the wall function, the computations of two turbulent incompressible flows are carried out. One is the flow past a flat plate and the other over a flame holder. As an application to the three-dimensional flow, a laminar flow in a driven cubic cavity is calculated. All the numerical results obtained here are compared with experimental data or other numerical results available in the literature.
Show less - Date Issued
- 1993
- PURL
- http://purl.flvc.org/fcla/dt/12330
- Subject Headings
- Navier-Stokes equations--Numerical solutions--Data processing, Algorithms, Flows (Differential dynamical systems)
- Format
- Document (PDF)
- Title
- The inviscid interaction of a jet and a plate in the two-dimensional configuration by hodograph method.
- Creator
- Lu, Jianqiang., Florida Atlantic University, Chow, Wen L., College of Engineering and Computer Science, Department of Ocean and Mechanical Engineering
- Abstract/Description
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In the present study, the problem of inviscid interaction between a jet and a solid plane wall has been examined. It is shown that this category of the problem is governed by the mechanisms of inviscid interaction. The method of hodograph transformation has been employed to formulate the problem, and the solution is obtained from numerical computations in the hodograph plane. The flow pattern in the physical plane is produced from additional integrations. It is demonstrated that the method of...
Show moreIn the present study, the problem of inviscid interaction between a jet and a solid plane wall has been examined. It is shown that this category of the problem is governed by the mechanisms of inviscid interaction. The method of hodograph transformation has been employed to formulate the problem, and the solution is obtained from numerical computations in the hodograph plane. The flow pattern in the physical plane is produced from additional integrations. It is demonstrated that the method of hodograph transformation is extremely suitable for solving problems of this type. The usefulness of the hodograph transformation to other problems of the similar nature is also mentioned.
Show less - Date Issued
- 1995
- PURL
- http://purl.flvc.org/fcla/dt/15140
- Subject Headings
- Hodograph equations, Inviscid flow--Mathematical models, Jets--Fluid dynamics
- Format
- Document (PDF)
- Title
- Experimental and theoretical studies of cryogenic sealing.
- Creator
- Jia, Lin X., Florida Atlantic University, Chow, Wen L., College of Engineering and Computer Science, Department of Ocean and Mechanical Engineering
- Abstract/Description
-
Funded by NASA Kennedy Space Center, this research project was to solve the liquid hydrogen leakage problem in the cryogenic system of Columbia space shuttle. A contracting-expanding self-sealing (CESSC) device was developed by making use of the thermal contraction ratio of dissimilar metals. A research cryostat providing with a high pressure and variable temperature test chamber was built to leak check the cryogenic fittings. A cryogenic research laboratory for the project was established in...
Show moreFunded by NASA Kennedy Space Center, this research project was to solve the liquid hydrogen leakage problem in the cryogenic system of Columbia space shuttle. A contracting-expanding self-sealing (CESSC) device was developed by making use of the thermal contraction ratio of dissimilar metals. A research cryostat providing with a high pressure and variable temperature test chamber was built to leak check the cryogenic fittings. A cryogenic research laboratory for the project was established in the Department of Mechanical Engineering, Florida Atlantic University. Both NASA KC126 fitting and the CESSC fitting were tested in the cryogenic testing system. A theoretical approach was also attempted to study the cryogenic leaking phenomenon. A finite element code was developed to simulate the thermal contraction for different CESSC designs. The ANSYS code was also used for the same purpose. The CESSC fittings were successfully used in the space program as well as in the superconducting projects. The principle of the CESSC seal has been extended to solve a variety of problems in cryogenic field.
Show less - Date Issued
- 1996
- PURL
- http://purl.flvc.org/fcla/dt/12448
- Subject Headings
- Sealing (Technology), Low temperature research
- Format
- Document (PDF)