3 edition of **The effect of three-dimensional freestream disturbances on the supersonic flow past a wedge** found in the catalog.

The effect of three-dimensional freestream disturbances on the supersonic flow past a wedge

- 354 Want to read
- 38 Currently reading

Published
**1997** by Institute for Computer Applications in Science and Engineering, NASA Langley Research Center, National Technical Information Service, distributor in Hampton, VA, [Springfield, Va .

Written in English

- Supersonic flow.,
- Uniform flow.,
- Wedges.,
- Shock waves.,
- Free flow.,
- Fourier series.,
- Aerodynamic characteristics.,
- Aerodynamic stability.

**Edition Notes**

Other titles | Effect of three dimensional freestream disturbances on the supersonic flow past a wedge. |

Statement | Peter W. Duck, D. Glenn Lasseigne, M.Y. Hussaini. |

Series | ICASE report -- no. 97-26., NASA contractor report -- 201698., NASA contractor report -- NASA CR-201698. |

Contributions | Lasseigne, D. Glenn., Hussaini, M. Yousuff., Institute for Computer Applications in Science and Engineering. |

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

Format | Microform |

Pagination | 1 v. |

ID Numbers | |

Open Library | OL15485941M |

Exact Solution for Flow Past a Cone In plane supersonic flow a class of simple-wave solutions (PrandtlMeyer flow, Chapter 15) was found, defined by the property that the two velocity components should be functions of each other. Simulation of Dispersionless Injections and Drift Echoes of Energetic Electrons Associated with Substorms Xinlin Li,1 D. N. Baker,1 M. Temerin,2 G. D. Reeves,3 R. D. Belian3 Abstract. The term “dispersionless injection” refers to a class. Mueller, Astrid M. () Mechanism of laser-induced bulk and surface defect generation in ZnO and TiO_2 nanoparticles: Effect on photoelectrochemical performance. In: th American Chemical Society National Meeting & Exposition, August , Boston, MA. Computational Fluid Dynamics C. Groth D. W. Zingg (Editors) Computational Fluid Dynamics Proceedings of the Third International Conference on Computational Fluid Dynamics, ICCFD3, Toronto, July With Figures and 47 Tables. Professor Clinton Groth Professor David W. Zingg University of Toronto Institute of Aerospace Studies Dufferin Street M3H 5T6 Downsview.

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Get The effect of three-dimensional freestream disturbances on the supersonic flow past a wedge book from a library. The effect of three-dimensional freestream disturbances on the supersonic flow past a wedge: NASA contract no. NAS [Peter W Duck; D G Lasseigne; M Yousuff Hussaini; Institute for Computer Applications in Science and Engineering.].

The effect of three-dimensional freestream disturbances on the supersonic flow past a wedge. Physics of Fluids, 9 (2), Stability of a Non-orthogonal Stagnation Flow to Three Dimensional Disturbances Oral Presentation presented at Program of the Division of Fluid Dynamics.

Supersonic Wedge Flow: Study #3. Figure 1. The shading of the Mach number for the Mach flow past a 15 degree wedge with the creation of an oblique shock. Introduction. This study is an example study demonstrating the computational process for a supersonic flow past a wedge with a comparison of the results with analytical results.

Disturbance evolution in the leading-edge region of a blunt flat plate in supersonic flow. The Effect of Three-Dimensional Freestream Disturbances on the Supersonic Flow Past a Wedge. Article. The effect of three-dimensional freestream disturbances on the supersonic flow past a wedge.

Physics of Fluids, 9, DUCK, P. W., LASSEIGNE, D. G., & Hussaini, M. On the interaction between the shock wave attached to a wedge and freestream disturbances.

THEORETICAL AND COMPUTATIONAL FLUID DYNAMICS, 7, The three-dimensional features of the field of the disturbances reflected from the shock are illustrated with reference to several examples. Keywords heat source supersonic flow Mach number shock wave wave equation pressure disturbance mechanical action disturbance reflection from a shockAuthor: S.

Arafailov. An analysis is presented for calculating the steady three-dimensional flow field in supersonic mixed-compression inlets at incidence. A zonal modeling approach is employed to obtain the solution. An algorithm is devised for calculating by the finite difference method the supersonic flow region for three-dimensional steady-state flow of a viscous gas past a blunted body with many contour discontinuities.

The state of this gas at high hypersonic flight speeds can be characterized by equilibrium or frozen physicochemical processes.

Generally speaking, any arbitrary number and sequence of Author: A. Antonets. ADVANCES IN APPLIED MATHEMAT () Existence of Local Solution to Supersonic Flow Past a Three-Dimensional Wing SHUXING CHEN Institute of Mathematics, Fudan University, Shanghai, China When a wing with a sharp leading edge is placed in a supersonic flow with a small attack angle, then a shock front appears and attaches to the leading by: Two-dimensional supersonic flow past a wedge can be described bearing the shock polar in mind.

For an attached plane wave, the wedge semi-vertex angle Δ, say, Fig.must be less than or equal to the maximum deflection angle δ m a x given by point F of the polar.

The shock wave then sets itself up at the angle given by the weaker shock. The maximum amplification of O (10 3) is achieved for streamwise independent disturbances due to the “lift-up effect,” as is the case of three-dimensional single-fluid flow.

In contrast to two-dimensional flows, where the adjoint of the leading mode influences the growth, the three-dimensional single-fluid flow growth is influenced by the Cited by: Supersonic flow past a three-dimensional cavity is studied numerically.

The streamwise length, depth and spanwise length of the cavity are 20 mm, 10 mm, and 10 mm, respectively. The length-to-depth ratio (𝐿/) for the cavity is 2. The width-to-depth ratio (𝑊/) is 1.

The cavity is three-dimensional. Two- And Three-Dimensional Flow of Air Through Square-Edged Sonic Orfaces (Chemical Engineering Dissertation, ) [Jr. Alexander Weir] on *FREE* shipping on qualifying offers. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Analysis of Force Production by a Biologically Inspired Underwater Flapping Foil Near Solid Boundaries in Three Dimensional Flow Dane Elles University of Rhode Island, [email protected] effect compared to the freestream.

It was also found that for the kinematic conditions. A First Course on Aerodynamics In a supersonic flow disturbances can propagate a) upstream b) downstream c) in all possible directions d) none of the above 5. For supersonic flow at freestream Mach number M ∞ past a two dimensional wedge of semi wedge angle θ.

Finite kinetics are incorporated as described by Eq. (G9). The program (BLOOM) is versatile in that it can calculate the flow quantities for several subsonic and/or supersonic freestream Mach numbers, heat release distributions, relaxation rates, and freestream flow properties in a single computer run.

What is meant by Supersonic flow. The flow of a fluid over a body at speeds greater than the speed of sound in the fluid, i.e. the flow region above mach is called as supersonic flow. The flow in which the shock waves start at the surface of the body.

The term supersonic is used to define a speed that is over the speed of sound. Numerical Simulation of Three-Dimensional Wave Packet in Supersonic Flow over a Compression Corner. Intermittency Behaviour in the Flow Past an Oscillating Airfoil.

The effect of the blade chord length on the aerodynamics of the MAV scale cycloidal propeller under hovering status. We present the results of an experimental investigation for controlling a shallow cavity flow in the Mach number range – The flow exhibits the characteristic staging behavior predicted by the semi-empirical Rossiter formula with multiple modes in the Mach number range – and a single strong mode in other Mach numbers.

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In other words, before the production of the Λ-vortex structure, there exists a kind of three-dimensional wave structure, which is the main cause of the Λ-vortex.

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10). Full text of "NASA Technical Reports Server (NTRS) A cumulative index to the issues of Aeronautical Engineering" See other formats. Download free eBooks at Pleaseclicktheadvert A First Course on Aerodynamics 5 Contents 3 Fundamentals of Viscous Flow 66 Introduction 66 Exact Viscous Flow Solutions 67 Introduction to Boundary Layer 76 Multiple Choice Questions 80 Figures 82 4 Wind Tunnels and a Few Basic Experiments 84 Introduction 84 Dal V.

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Edwards and James F. Meyers, An Overview of Particle Sampling Bias, Second International Symposium on Applications of Laser Anemometry to Fluid Mechanics, Lisbon, Portugal, July A Subsonic, inviscid flow (elliptic type) B Supersonic, inviscid flow (hyperbolic type) C Boundary-layer flow (parabolic type) Fig.

A z o n a l m e t h o d for f l o w c a l c u l a t i o n for S p a c e S h u t t l e Orbiter, as t a k e n from Ref. zones, as shown in Fig. as follows: A. Characterization of Freestream Disturbances in Conventional Hypersonic Wind Tunnels.

Duan, Lian Analysis of pressure perturbation sources on a generic space launcher after-body in supersonic flow using zonal turbulence modeling and dynamic mode decomposition Three-dimensional flow measurements inside the cylinder of a four-value.

The contents of this book covers the material required in the Fluid Mechanics Graduate Core Course (MEEN) and in Advanced Fluid Mechanics, a Ph. D-level elective course (MEEN), both of which I have been teaching at Texas A&M University for the past two decades.

What effect would tripling all the dimensions of a triangular prism have on the volume of the prism. Complete the explanation. If both the base and height of the triangular base are tripled, the area of the base is multiplied by _____.

Tripling the height of the prism as well means the volume of the prism is multiplied by _____. Direct numerical simulations of three-dimensional hypersonic flow over a flat plate with periodic holes.

(Technical report). University of Southampton. Castagna, J., & Sandham, N. Direct numerical simulation of a sonic round jet in a turbulent supersonic cross flow. (School of Engineering Sciences AFM Technical Reports; No.

10/01). together with a new quasi-periodic three-dimensional mode which can manifest either as standing waves, or spanwise travelling waves that are modulated by the periodic base ﬂow.† Of these two, only the travelling-wave solutions are stable.

Flow geometry, dimensionless groups, and symmetries. B Subsonic Compressible Flow c Supersonic Flow D Summary Supersonic Wind Tunnels and Rocket Engines Discussion on Compressibility Introduction to Viscous Flow Results for a Laminar Boundary Layer Results for a Tubulent Boundary Layer Transition Flow Separation Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A continuing bibliography with indexes (supplement )" See other formats.

For a given wedge angle, the flow field is governed by the porosity of the wedge surface as well as the ``illumination angle'' of the perforation holes.

The latter parameter is crucial for obtaining a uniform velocity distribution at the wedge base, and can be adjusted by varying the surface thickness or the aspect ratio of the perforation holes. Velocity Since most liquids are practically incompressible the relation between the quantity flowing past a given point in a given time and the velocity of flow is expressed as follows: Q Av This relationship in SI units is as follows: v for circular conduits Q/d 2 where v average velocity of flow m/s Q quantity of flow m 3 /h.

Content Posted in PDF. Costliest Year Ever for Weather-Related Disasters, Betsy Hnath. PDF. State of the Commonwealth Report, Vinod Agarwal, Barbara Blake, Ethan Crouson, Steve Daniel, Nikki Johnson, James V.

Koch, Tim Komarek, Feng Lian, Sharon Lomax, Janet Molinaro, Isaiah Smith, Jay Walker, Hannah White, Ziniya Zahedi, and Robert McNab. View Notes - Lecture 9 - Depth Volume Sophie(1) from RTV at Florida State University. Chapter 9 The Three-Dimensional Field: Depth and Volume Depth & Volume TV and film require us to project a.

Oscillations and Vacuum to the Three-Dimensional Isentropic Compressible Navier-Stokes Equations∗ Xiangdi HUANGa,c,JingLIb,c, Zhouping XINc a Department of Mathematics, University of Science and Technology of China, HefeiP.

China b Institute of Applied Mathematics, AMSS, Academia Sinica, BeijingP. China. Anderson and˙fm Decem McGraw-Hill Series in Aeronautical and Aerospace Engineering John D. Anderson, Jr., University of Maryland, Consulting Editor A. FIGURE COHERENCE IN THE KINETIC DEPTH EFFECT BERT F.

GREEN, JR. Lincoln Laboratory,1 Massachusetts Institute of Technology When an observer views the two-dimensional (2-D) projection, e.g., shadow, of a moving three-dimen-sional (3-D) object, he usually per-ceives the shadow pattern as a form with depth.

This has been called the Kinetic Depth. Proc. SPIE24th International Congress on High-Speed Photography and Photonics, pg 1 (17 April ); doi: /() is reduced to: ()which is the Bernoulli equation Some Discussions on Navier-Stokes EquationsThe flow in engineering applications, such as in a turbine, a compressor or acombustion engine is characterized by a three-dimensional, highly unsteady motionwith random fluctuations due to the interactions between the stator and rotor.Of particular interest for supersonic calculations past air-breathing missile configurations is the capability of the method to calculate 'superinclined' panels (9), i.e.

elements whose surface is more inclined to the freestream velocity than the (asymptotic) Mach angle.