Design and Navier-Stokes analysis of hypersonic wind tunnel nozzles

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National Aeronautics and Space Administration] , [Washington, DC
Wind tunnels., Nozzles., Navier-Stokes equat
Other titlesDesign and Navier Stokes analysis of hypersonic wind tunnel nozzles.
Statementby James R. Benton.
SeriesNASA-CR -- 185500., NASA contractor report -- NASA CR-185500.
ContributionsUnited States. National Aeronautics and Space Administration.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL18033265M

Navier-Stokes and Euler codea developed for supersonic and hypersonic flow analysis generally hold upstream boundaries con- stant at -me uniform freestream condition. So, the ability to deliver uniform flow grants the hypersonic wind tunnel the additional objective of validating computer solutions.

Design and Navier-Stokes analysis of hypersonic wind tunnel nozzles (SuDoc NAS ) [James R. Benton] on *FREE* shipping on qualifying : James R. Benton. Four hypersonic wind tunnel nozzles ranging in Mach number from 6 to 17 are designed with the method of characteristics and boundary layer approach (MOC/BL) and analyzed with a Navier-Stokes solver.

Limitations of the MOC/BL approach when applied to thick high speed boundary layers with non-zero normal pressure gradients are : James R.

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Benton. Four hypersonic wind tunnel nozzles ranging in Mach number from 6 to 17 are designed with the method of characteristics and boundary layer approach (MOC/BL) and analyzed with a Navier-Stokes solver. Limitations of the MOC/BL approach when applied to thick high speed boundary layers with non-zero normal pressure gradients are investigated.

Two specific problems are considered. The first problem is the automated design of the supersonic portion of a quiet hypersonic wind tunnel. Modern optimization software is combined with full Navier-Stokes simulations and PSE stability analysis to design a Mach 6 nozzle Cited by: 3.

Books. AIAA Education Series; Library of Flight; Progress in Astronautics and Aeronautics; The Aerospace Press; Browse All Books; Meeting Papers; Joint Propulsion Conferences Home; No Access.

Aerodynamic design modification of a hypersonic wind tunnel nozzle by. Design of a Mach-6 quiet-flow wind-tunnel nozzle using the e**N method for transition estimation.

A design program is developed which incorporates a modern approach to the design of supersonic/hypersonic wind-tunnel nozzles. The approach is obtained by the coupling of computational fluid. Symmetrical two-dimensional nozzles were designed for the supersonic wind-tunnel, in the Department of Mechanical Engineering, analytical and semi­ graphical methods obtained from the theory of Characteristics.

These nozzles, designed for an optimum running time of 30 seco~s, ~~Mach number of 2, investigate the behavior of jet engines and military aircrafts.

Hypersonic wind tunnels find their applications in rockets and space vehicles. A further way to categorize low speed wind tunnels is by dividing them into open loop or closed loop wind tunnels [3].

The open loop wind tunnels are usually working on suction type flow induced by axial. Design and evaluation of a wind-tunnel with expanding corners 3 L), was built in and is still used for aeronautical research.

It has a 3 m long test section of 2 2 m2 cross section and a maximum speed of 62 m/s. A supersonic, a hypersonic and a ballistic wind-tunnel are also part of the early aeronautical research history at KTH.

A new procedure to design the contour of an axisymmetric hypersonic wind tunnel nozzle is presented. The method may be generally categorized as Navier-Stokes-based design by analysis.

Details Design and Navier-Stokes analysis of hypersonic wind tunnel nozzles PDF

Get this from a library. Design and Navier-Stokes analysis of hypersonic wind tunnel nozzles. [James R Benton; United States. National Aeronautics and Space Administration.]. I have previously covered some of the analysis used to design the throat section of the wind tunnel, this time I shall cover some of the design used for the rest of the tunnel design.

The idea was to use a pressure vessel coupled to a large diameter ball valve, so that large volumes of high pressure air can be dumped through the tunnel. As the core component of a wind tunnel, the supersonic nozzle controls the expansion of high-pressure gas to produce a desired Mach number with high flow quality at the test area of the wind tunnel.

However, the current state of the art in wind tunnel nozzles limits the Mach number to a fixed value during a test run [1]. A moveable block planar nozzle wind tunnel design from the University of Michigan in was shown with previous analysis to operate between Mach 1 and at least Mach for mid-size test sections, with continuous variation in Mach number and accounting for limitations governed by supply temperature and pressure, liquefaction, flow rate, and flow quality for a desired dynamic pressure or.

Key words: hypersonic nozzle, Navier–Stokes equations, Euler equations, method of character-istics, numerical optimization. Introduction. It is known that a good quality of the wind-tunnel flow is ensured by using carefully designed nozzles accelerating the gas flow to a specified velocity.

Almost all existing wind tunnels use unimodal. and PSE stability analysis to design a Mach 6 nozzle with maximum quiet test length. response surface is constructed from a user-specified set of contour shapes and a genetic.

algorithm is used to find the “optimal contour”, which is defined as the shortest nozzle with. the maximum quiet test length. Two specific problems are considered. The first problem is the automated design of the supersonic portion of a quiet hypersonic wind tunnel.

Modern optimization software is combined with full Navier-Stokes simulations and PSE stability analysis to design a Mach 6 nozzle. Simplified Navier-Stokes equations have found application as an alternative to the complete Navier-Stokes equations for the simulation of viscous gas flows in regions of large dimensions, when there is a predominant direction of the flow [1–4].

In the present paper, flows in wind tunnel nozzles are investigated on the basis of this model. Flows in conical and profiled axisymmetric hypersonic. This real gas procedure divides the nozzle into four distinct parts: subsonic, throat to conical, conical, and turning flow regions.

The design process is greatly simplified by treating the imperfect gas effects only in the source flow region. This simplification can be justified for a large class of hypersonic wind tunnel nozzle design problems.

An improved version of the CSCM implicit Navier-Stokes solver with a flexible data structure has been applied, in conjunction with a sophisticated patched grid system, to the aerodynamic analysis of hypersonic axisymmetric contoured nozzles of the NASA-Ames foot hypersonic wind tunnel.

The results obtained are found to be in good agreement with experiment. Wind Tunnels: Design / Construction, Types and Usage Limitations (Mechanical Engineering Theory and Applications) [Chaplin, Susan B.] on *FREE* shipping on qualifying offers.

Wind Tunnels: Design / Construction, Types and Usage Limitations (Mechanical Engineering Theory and Reviews: 1. hypersonic wind-tunnel nozzles, J. of Propulsion and Power, 8, No. 5 (), pp. [2] G. Dupeyrat, J. Marquette and B. Rowe, Design and testing of axisymmetric nozzles for ion‐molecule reaction studies between 20 °K and °K, Phys.

Flu (). of the wind tunnel. DESIGN OF WIND TUNNEL COMPONENTS a. Design of the Converging Diverging Nozzle Converging diverging nozzle is designed using the method of characteristics. It is the most frequently used method for defining internal contour of supersonic nozzle.

The design is based on isentropic conditions and Prandtl-Meyer expansion.

Description Design and Navier-Stokes analysis of hypersonic wind tunnel nozzles PDF

A new concept for nozzle design is presented which promises a large increase in the length of the quiet test core. The Advanced Mach Axisymmetric Quiet Nozzle is the first prototype built to prove the new design. Development of a Quiet Supersonic Wind Tunnel with a Cryogenic Adaptive Nozzle Dr.

Stephen D. Wolf (NA%A-CR) DEVELOPMENT OF A QUIET Nqi-Z SUPERSONIC WIND TUNNEL WITH A CRYOGENIC AqAPTIV_ NOZZLE Annual Progress Report_ May - Apr. (MCAT Inst.) p unclas CSCt 14B G3/09 February / MCAT Institute Blue Gum Drive. nozzle. The inviscid design of a supersonic (and hypersonic) wind tunnel nozzle for a perfect gas was originated by Busseman in the s (as noted in Ref.

1) and, in the opinion of the author, was finally perfected by Sivells2 in the s. No similar progress has been made for real gas wind tunnel nozzle design.

This paper concentrates on an. Design and operation of a continuous-flow hypersonic wind tunnel using a two-dimensional nozzle. [Paris] North Atlantic Treaty Organization, Advisory Group for Aeronautical Research and Development, (OCoLC) Material Type: Government publication, International government publication: Document Type: Book: All Authors / Contributors.

The paper involves a design of Mach 5 Nozzle from an existing Mach 6 Nozzle of a large Hypersonic Wind Tunnel in Vikram Sarabhai Space Centre, Thiruvananthapuram in order to obtain the simulation of Mach 5.

The work deals with design of nozzle contour using specific boundary conditions, where by. A hypersonic wind tunnel is designed to generate a hypersonic flow field in the working section, thus simulating the typical flow features of this flow regime - including compression shocks and pronounced boundary layer effects, entropy layer and viscous interaction zones and most importantly high total temperatures of the flow.

The speed of these tunnels vary from Mach 5 to The power requirement of a wind tunnel increases .Nozzle Design for the Supersonic Wind Tunnel Ramjet Attachment A Senior Project presented to the Faculty of the Aerospace Departmentand the height and width of the wind tunnel.

In this analysis section the numbers shown in Fig. 5 will signify the performance parameter’s location along the nozzle.CHAPTER 2 LITERATURE REVIEW INTRODUCTION A wind tunnel is a tool used in aerodynamic research to study the effects of air moving past solid objects.

A wind tunnel consists of a closed tubular passage with the object under test mounted in the middle. A powerful fan system moves air past the object; the fan must have straightening vanes to.