Three-dimensional upwind parabolized Navier-Stokes code for supersonic combustion flowfields

Wadawadigi, Ganesh; Tannehill, John C.; Buelow, Philip E.; Lawrence, Scott L.

doi:10.2514/3.475

Cited by 16 publications

(3 citation statements)

References 26 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The computer code developed through the NASP program was commercialised to appear as the GASP, and remains even today as a mainstay for high-temperature aerodynamic predictive tool for a wide range of engineering applications. The parabolised Navier-Stokes code for supersonic combustion was developed by Tannehill et al to support the NASP (76)(77)(78) . This computer code was actually adopted in performing the nose-to-tail analysis for the scramjet propulsive system.…”

Section: The 1980smentioning

confidence: 99%

Computational fluid dynamics application to aerospace science

Shang

2009

Aeronaut. j.

View full text Add to dashboard Cite

critical stability criterion for finite-difference approximation and addressed the issue of resolving hydrodynamic shock as early as 1944 and his more accessible article in the literature was published six years later (2,3) . Under the similar war time security restriction, the spherical blast wave computation by G. I. Taylor was also delayed for public release until 1950 (4) . These pioneering works were performed to meet an urgent engineering need which set a pattern of science and technology development for practical applications.Harlow and his colleagues developed the particle in cell(PIC) method based on a combination Lagrangian-Eulerian description of the fluid motion (5) . The PIC method has showed how well suited it was to study time-dependent and multi-dimensional fluid motion. The effectiveness of this method is demonstrated through the applications to shock interaction, supersonic wakes, and hypersonic sharp leading-edge flows. This method is still in use today for Magneto-hydrodynamic research. At the same time, Hirt made a lasting contribution to turbulent transport properties simulation by highlighting the numerical challenges and providing guidance for future research (6) . All these accomplishments were accompanied by exhaustive proof in order to illustrate the validity of the approximations and the numerical accuracy. This rigorous process actually established the standards for all future CFD algorithm and numerical procedure research. The detailed derivation of formulations and extensive discussions on computational accuracy and limits of applicability became the accepted standard in CFD research. During that time, all valuable information was largely unknown to the aerospace science community. ABSTRACTA brief narration on significant accomplishments in computational fluid dynamics (CFD) for basic research and aerospace application is attempted to highlight the outstanding achievements by scientists and engineers of this discipline. To traverse such a vast domain, numerous and excellent contributions to CFD will be unintentionally overlooked by the author's limited exposure. Nevertheless it is an ardent hope that the present abridged literature review will aid to reaffirm excellence in research and to identify knowledge shortfalls both in aerodynamics and its modeling and simulation capability. The future modeling and simulation technology needs, as well as potential and fertile research areas, are humbly put forth for consideration.

show abstract

Section: The 1980smentioning

confidence: 99%

Computational fluid dynamics application to aerospace science

Shang

2009

Aeronaut. j.

View full text Add to dashboard Cite

show abstract

“…The 3-D UPS code was extended to permit equilibrium and nonequilibrium airflow computations by TannehiU et al [34] and Buelow et al [35], respectively. Recently, the code has been enhanced to include internal flows with hydrogen-air chemistry [36], k -e turbulence modelling [37], finite-cataljrtic wall boundary conditions [38], and vibrational and elec tronic nonequilibrium effects [39]. In addition, the upwinding used for the approximate Riemann solver has been modified to allow upwinding in the subsonic regions [40,41].…”

Section: Ups Codementioning

confidence: 99%

PNS algorithm for solving supersonic flows with upstream influences

Miller

Tannehill

Lawrence

1998

36th AIAA Aerospace Sciences Meeting and Exhibit

View full text Add to dashboard Cite

This manuscript has been reproduced from the microfilm master. UMI films the text direct^ from the original or copy submitted. Thus, some thesis and dissertation copies are in typewriter fiice, i;^e others may be from any type of computer primer. In the unlikely event that the author did not send UMI a complete manuscript and there are missing pages, these will be noted. Also, if unauthorized copyright material had to be removed, a note will indicate the deletioiL Oversize materials (e.g., maps, drawings, charts) are reproduced by sectioning the original, b^inning at the upper left-hand comer and continuing from left to right in equal sections with small overijq)s. Each original is also photographed in one exposure and is included in reduced form at the back of the book.

show abstract

Section: Ups Codementioning

confidence: 99%

PNS algorithm for solving supersonic flows with upstream influences

Miller

View full text Add to dashboard Cite

The qualiQr of this reproduction b dependent upon the quality of the copy submitted. Broken or indistinct print, colored or poor quality illustrations and photographs, print bleedthrough, substandard margins, and improper alignment can adverse^ afifect reproduction. In the unlikely event that the author did not send UMI a complete manuscript and there are missing pages, these will be noted. Also, if unauthorized copyright material had to be removed, a note will indicate the deletioiL Oversize materials (e.g., maps, drawings, charts) are reproduced by sectioning the original, b^inning at the upper left-hand comer and continuing from left to right in equal sections with small overijq)s. Each original is also photographed in one exposure and is included in reduced form at the back of the book.

show abstract

Three-dimensional upwind parabolized Navier-Stokes code for supersonic combustion flowfields

Cited by 16 publications

References 26 publications

Computational fluid dynamics application to aerospace science

Computational fluid dynamics application to aerospace science

PNS algorithm for solving supersonic flows with upstream influences

PNS algorithm for solving supersonic flows with upstream influences

Contact Info

Product

Resources

About