2 edition of **improved supersonic, three-dimensional, external, inviscid flow field code** found in the catalog.

improved supersonic, three-dimensional, external, inviscid flow field code

Frank Marconi

- 381 Want to read
- 29 Currently reading

Published
**1978** by National Aeronautics and Space Administration, Scientific and Technical Information Office, for sale by the National Technical Information Service in [Washington], Springfield, Va .

Written in English

- Aerodynamics, Supersonic -- Data processing

**Edition Notes**

Statement | Frank Marconi and Frank Koch, Grumman Aerospace Corporation |

Series | NASA contractor report ; NASA CR-3108, NASA contractor report -- NASA CR-3108 |

Contributions | Koch, Frank, 1931-, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Langley Research Center, Grumman Aerospace Corporation |

The Physical Object | |
---|---|

Pagination | iv, 25 p. : |

Number of Pages | 25 |

ID Numbers | |

Open Library | OL14930267M |

Boundary layer and wake modifications to compressor design systems: the effect of blade-to-blade flow variations on the mean flow field of a transonic rotor: final report, 01 September August / (Wright-Patterson Air Force Base, Ohio: Air Force Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force. A Regularized Inviscid Vortex Sheet Method for Three Dimensional Flows With Density Interfaces by Mark Joseph Stock A dissertation submitted in partial fulﬁllment of the requirements for the degree of Doctor of Philosophy (Aerospace Engineering) in The University of Michigan Doctoral Committee: Professor Werner J. A. Dahm, Co-Chair. Great efforts have been dedicated during the last decades to the research and development of hypersonic aircrafts that can fly at several times the speed of sound. These aerospace vehicles have revolutionary applications in national security as advanced hypersonic weapons, in space exploration as reusable stages for access to low Earth orbit, and in commercial aviation as fast Cited by: A Parallel High-Order CENO Finite-Volume Scheme with AMR for Three-Dimensional Ideal MHD Flows. Spectral and High Order Methods for Partial Differential Equations ICOSAHOM , () A high-order flux reconstruction method with adaptive mesh refinement and artificial diffusivity on unstructured moving/deforming mesh for shock by:

Readers are introduced to fundamental algorithms (with Fortran source code) for basic applications, such as subsonic lifting airfoils, transonic supercritical flows utilizing mixed differencing, models for inviscid shear flow aerodynamics, and so on - models they can extend to include newer effects developed in the second half of the book.

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An Improved Supersonic, Three-Dimensional, External, Inviscid Flow Field Code Frank Marconi and Frank Koch Grumman Aerospace Corporation Bethpage, New York Prepared for Langley Research Center under Contract NASl NASA National Aeronautics and Space Administration Scientific and Technical Information Office.

Cited by: 6. Improved supersonic, three-dimensional, external, inviscid flow field code. [Washington]: National Aeronautics and Space Administration, Scientific and Technical Information Office. plete viscous and inviscid flow field about delta wings.

Moreover, solu-tions are obtained without the costly computing requirements of a fully three-dimensional, time-dependent, finite-difference technique.

In the first approach, the flow is assumed to be conically self-similar. This approximation is suggested by the results of experiments forFile Size: 1MB.

JOURNAL OF COMPUTATIONAL PHYS () Supersonic Inviscid Flow A Three-Dimensional Characteristics Approach JEFFERSON FONG* Supercomputer Computations Research Institute, Florida State University, Taliahassee, Florida AND LAWRENCE SIROVICK^ Division of Applied Mathematics, Brown University, Providence, Rhode Island Author: Jefferson Fong, Lawrence Sirovich.

MacCormack, R. W., and Warming, R. F., “Survey of Computational Methods for Three-Dimensional Supersonic Inviscid Flow with Shocks,” AGARD Lecture Series No. 64 on Advances in Numerical Fluid Dynamics, AGARD-LS, Google ScholarCited by: Abstract.

In the area of inviscid compressible flows there are a variety of practical problems that arise in everyday engineering applications. These include rocket nozzle flows, aircraft and missile engine inlet flows, reentry vehicle and rocket aerodynamics, blast fields generated by different types of energy release, and aircraft flow by: 4.

Three-Dimensional Supersonic Viscous Flow (AOFA) To use this method it is necessary to first determine an initial data point in a region where the inviscid improved supersonic of the flow is supersonic. Downloadcontaining the original source code and the source code. Steps in the construction of a Delaunay tessellation using the Bowyer/Watson algorithm in two-dimensions.

Solution of 3-D supersonic flowfields via adapting unstructured meshes MATHEMATICAL MODEL AND NUMERICAL DISCRETIZATION The Euler equations provide a mathematical model inviscid flow field code book the flow of an inviscid compressible by: A 'read' is counted each time someone views a publication summary (such as the title, abstract, and list of authors), clicks on a figure, or views or downloads the full-text.

Three Dimensional Interaction Flow Field in a Supersonic Inlet like Configuration. Three Dimensional Interaction Flow Field in a Supersonic Inlet like Configuration at Mach 4 19th 20th Mar 3rd Wind tunnel testing conference. DRDL, Hyderabad. Three-Dimensional Building-Cube Method for Inviscid Compressible Flow Computations Article in International Journal of Precision Engineering and Manufacturing 16(13).

plete viscous and inviscid flow field about delta wings. Moreover, solu tions are obtained without the costly computing requirements of a fully three-dimensional, time-dependent, finite-difference technique.

In the first approach, the flow is assumed to be conically self-similar. This approximation is suggested by the results of experiments for. It is clear that this flow has a three dimensional aspects, in spite of the high hub/tip ratio which has theoretically a two-dimensional flow aspects.

Keywords: 3-D unsteady inviscid flow, axial turbine stage, nozzle-rotor interaction. THREE DIMENSIONAL BOUNDARY LAYER TRANSITION ANALYSIS IN SUPERSONIC FLOW USING A NAVIER-STOKES CODE (NS) analysis are summarized in section 2. The results of transition analysis on the sharp cone, the nose cone, and the natural laminar flow wing of the experimental airplane are described in section 3, 4 and 5 respectively.

Steady-state Analysis of Supersonic Mixing Enhanced by a Threedimensional Cavity Flow-(a) duct with a rectangle cavity (b) duct with a three-dimensional cavity pressure gradient across the bow shock wav. Fig. 4: Oil flow visualization16). Fig. 5: Limiting streamlines on the duct lower wall.

transversely into the primary flow. The coordinate. gradient of the inviscid external flow outside the boundary layer: e. ee ee. Udse, e s. y dy.

ρ ρ ξρμ ξ ρ == ∫∫ η, where. is the streamwise (along. s) velocity component outside the boundary layer and. μe is the viscosity). Assuming that the mean flow parameters are independent of, we can present the stream File Size: 1MB.

Investigation of Transonic Flow Behavior around a Three-Dimensional Turret Using Particle Image Velocimetry Carlos Caballero. College of Engineering, University of Florida. Light distortions produced by flow density gradients, commonly referred as aero-optic aberrations, remain one of the main sources of.

An improved second-order theory of inviscid supersonic flow past bodies of revolution. Supersonic flow over three-dimensional ablated nosetips using an unsteady implicit numerical procedure. Supersonic inviscid flow field computations of missile type bodies.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA CALCULATION OF INVISCID TRANSONIC FLOW OVER A COMPLETE AIRCRAFT ∗ A. Jameson, T.J. Baker and N.P. Weatherill Department of Mechanical Engineering Princeton University Princeton, New Jersey U.S.A.

We present preliminary results for the calculation of inviscid transonic ow over a complete aircraft.

The conceptual study by the Boeing Company suggests a two-dimensional inlet as an option (Ref. In addition to external compression of supersonic flow about axisymmetric or two-dimensional surfaces, it is possible to compress supersonic flow about “three-dimensional” surfaces through the process of streamline tracing.

Three-dimensional supersonic flow over a spike-nosed body of revolution. The characteristics of the flow field for a Mach number ofin this numerical investigation a full three-dimensional flow was considered to allow any asymmetry to develop in the cases of angles of attack larger than zero.

A three dimensional viscous/inviscid interactive boundary layer method for predicting the effects of fluid viscosity on the performance of fully wetted propellers is presented. This method is developed by coupling a three dimensional low-order potential based panel method and a two dimensional integral boundary layer analysis method.

Iterative solution of transonic flows over airfoils and wings, including flows at mach 1. Antony Jameson. Search for more papers by this author. /doi/book//MASM82 M. SICLARI Computation of nonlinear supersonic potential flow over three dimensional surfaces, ()., (). / Cited by: Alternatively, once a supersonic flow-field has been calculated by some non-characteristic methods, the characteristic lines can be calculated and superimposed and inferences about influences, causes and effects can be drawn.

The α and β or C+ and C− characteristics are inclined at ±μ to the local streamlines where μ = sin −1 (1/M).Author: Sannu Mölder. "The Problem of Three-Dimensional Lifting Potential Flow and Its Solution by Means of Surface Singularity Distributions", Computer Methods in Applied Mechanics and Engineering 4 () pp.

Carmichael, R.L., and Erickson, L.L., "PAN AIR - A Higher Order Panel Method for Predicting Subsonic or Supersonic Linear Potential Flows About. Mach with formation of a normal shock in the flow field where supersonic flow enters the normal shock and subsonic flow exits the shock.

This flow is a classic, fundamental supersonic flow whose analytic solution is exact and can be found in any compressible flow textbook, such as the book by Anderson [17].

“An Improved Higher Order Panel Method for Three-Dimensional Lifting flow,” Douglas Aircraft Co. Report No. NADC, Maskew, B., “Prediction of Subsonic Aerodynamic Characteristics: A Case for Lower Order Panel Methods,”. Transonic and Supersonic Flow Calculations Around Aircraft Using a Multidomain Euler Code p.

Simulation of 2D External Incompressible Viscous Flows by Means of a Domain Decomposition Method p. Domain Decomposition Combined with Adaptive Remeshing for Problems of Transient Compressible Flow p.

prehensive insight on the physical aspects of supersonic ﬂows in nanoscale rectangular channels that fall in the tran-sitional to free-molecular regimes. The simulations are per-formed with a three-dimensional, unstructured, DSMC U3DSMC code and this paper addresses also the pertinent computational aspects of the U3DSMC implementation.

Flow Field and Performance of a Centrifugal Compressor Rotor With Tandem Blades of Adjustable Geometry. A Design Study of Radial Inflow Turbines With Splitter Blades in Three-Dimensional Flow.

Tjokroamlnata, C. Tan, Part II — A Model for Supersonic Flow. König, D. Hennecke, L. Fottner. Three-Dimensional Supersonic Viscous Flow: public domain: Determine the viscous and inviscid flow about a body of revolution at angle of attack.

(work-in-progress) / AOFA: Tidy: public domain: A program for renumbering statements in a Fortran program. / TIDY: TIPSOD: data visualization: ToPy: GNU GPLv3. Investigation of the Supersonic Flow Field around a delta wing using Particle-Image-Velocimetry velocity components in the three-dimensional flow field.

The spatial development of leading edge vortices can In supersonic flow fields problems concerning the particle generation are caused by high velocities in the flow. Supersonic diffusers. See also what's at your library, or elsewhere. Broader term: Aerodynamics, Supersonic; Filed under: Supersonic diffusers Performance of a short annular dump diffuser using suction-stabilized vortices at inlet Mach numbers to / (Washington: National Aeronautics and Space Administration, Scientific and Technical Information Office ; Springfield, Va.

THE THREE-DIMENSIONAL SUPERSONIC BIPLANE WITH DIFFERENT PLANAR SHAPES. Yonezawa*, H. Yamashita* *Institute of Fluid Science, Tohoku University, Katahira, Aoba-ku, Sendai,Japan. Keywords: Supersonic flow, Supersonic biplane, Shock wave interaction.

Abstract. The supersonic biplane is well known for the. “Two- and Three-Dimensional Turbine Blade Row Flow Field Simulations,” Scientific Research Associates, Inc., SE Published by NASA Lewis Research Center in Turbine Engine Hot Section Technology Report, Octoberpp.

Analysis of three-dimensional supersonic nozzle exhaust flow fields. A second order numerical method employing reference plane characteristics has been developed for the calculation of geometrically complex three dimensional nozzle-exhaust flow fields, heretofore incalculable by existing methods.

containing the original source code. @article{osti_, title = {Numerical analysis of the three-dimensional swirling flow in centrifugal compressor volutes}, author = {Ayder, E and Van den Braembussche, R}, abstractNote = {The improvement of centrifugal compressor performance and the control of the radial forces acting on the impeller due to the circumferential variation of the static pressure caused by the Cited by: title = "Wake topology in a three-dimensional supersonic base flow", abstract = "The near wake of a blunt-base cylinder at 10° angle-of-attack to a Mach freestream flow is studied using Mie scattering flow visualization at several Cited by: 6.

This book contains chapters written by some eminent scientists and researchers on Computational Methods in Hypersonic Aerodynamics and forms a natural sequel to the earlier publications on Computational Methods in Potential Flow () and Computational Methods in Viscous Aerodynamics ().

Object of the present study is the turbulence modeling of flows with extensive crossflow separation, i.e., three-dimensional flows in which the separated boundary layer rolls up into longitudinal type of separation appears in many practical aerospace configurations; for example, subsonic/supersonic flow about slender bodies or delta wings at high incidence or Cited by: 7.Inviscid Flow The inviscid flow is calculated using the method of Rosen [2], i.e., the SPLASH computer code.

The method is an extended version of the basic panel method of Maskew [22, originally developed for the predic- tion of subsonic aerodynamic flows about arbitrary con- figurations, modified to include the presence of a free surface.The Proceedings: Fifth International Conference on Numerical Ship The algorithm used in this code and how it has been improved so far explained two important aspects of the computational fluid dy- namics (CFD) codes: efficiency and accuracy.

Pulliam, T. H. and Steger, J. L., "Implicit Fi- nite Difference Simulations of Three-Dimensional.