2 edition of Numerical Methods For Predicting Subsonic, Transonic and Supersonic Flow. found in the catalog.
Numerical Methods For Predicting Subsonic, Transonic and Supersonic Flow.
North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development.
|Series||Nato Agard ag -- 187|
|Contributions||Taylor, T., Yaggy, P.|
I am trying to solve unsteady flows with supersonic jets flowing in an external ambient (e.g. quiescent air or an external flow). At the outlet, the flow can have both supersonic and subsonic regions. Moreover, at the same point of the outlet boundary, the flow can switch from subsonic to supersonic because of the imping jet unsteady motions. In transonic flow there is an embedded region of locally supersonic flow inside an otherwise subsonic flow. The supersonic region is usually terminated by a shock discontinuity. The success of a numerical scheme for transonic flow prediction depends on its capability of capturing all the flow details and non-linearities including sharp shock Author: Natalie J.T. Phillips, John A. Gear, Hing Hung.
1) The numerical methods used in this paper can be accurately enough to simulate the wave and eddy structure in lateral jet interaction flowfield. Main structures of the lateral jet interaction flowfield are shown at subsonic, transonic and low supersonic conditions including jet bow shock, separate shock, λ-shape shock and so : Jin Chen, Yaofeng Liu, Jinglong Bo. [Mason] transonic aerodynamics of airfoils and wings 1. W.H. Mason 4/12/04 7. Transonic Aerodynamics of Airfoils and Wings Introduction Transonic flow occurs when there is mixed sub- and supersonic local flow in the same flowfield (typically with freestream Mach numbers from M = or to ).
Also addressed are: three-dimensional flow analysis of turboprop inlet and nacelle configurations, application of computational methods to the design of large turbofan engine nacelles, comparison of full potential and Euler solution algorithms for aeropropulsive flow field computations, subsonic/transonic, supersonic nozzle flows and nozzle. Numerical schemes for unsteady transonic flow calculation Ly, E , where the flows are characterised by the presence of adjacent regions of subsonic and supersonic flow, usually accompanied by weak shocks. It has been a common expectation that the numerical approach as an alternative to wind tunnel experiments would become more.
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Get this from a library. Numerical methods for predicting subsonic, transonic and supersonic flow. [Thomas D Taylor; P F Yaggy; North Atlantic Treaty Organization.
Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel.]. Subsonic, Transonic, and Supersonic Nozzle Flow by the Inverse Technique. DAVID J. NORTON ; DAVID J.
NORTON. Numerical Methods of Studying Nozzle Gas Flows. Irrotational Subsonic Flow of an Ideal Gas in Two-Dimensional Ducts Cited by: 5. Also addressed are: three-dimensional flow analysis of turboprop inlet and nacelle configurations, application of computational methods to the design of large turbofan engine nacelles, comparison of full potential and Euler solution algorithms for aero-propulsive flow field computations, subsonic/transonic, supersonic nozzle flows and nozzle Cited by: 4.
calculate the subsonic/supersonic flow through such cascades by analytical and numerical methods and to compare their results. If the flow is supersonic –and this is the case for the first stage of a transonic compressor- the flow is diffi-cult to calculate.
The reason for these difficulties are: • Supersonic flows contain shock and they. with other numerical results available in the literature. KEY WORDS Finite volume Compressible flow Subsonic flow Transonic flow Supersonic flow 1.
INTRODUCTION Most of the traditional numerical methods developed for compressible flow simulation use an unsteady form of the Navier-Stokes or Euler equations.'-6 These methods use density as theFile Size: 1MB.
In this study, the high-speed Numerical Methods For Predicting Subsonic supercavitating flows is investigated with numerical and theoretical method. The Primary findings include: (1) Results are shown for high-subsonic and transonic projectiles, there is a general agreement between the predicted cavity profiles and the experimental by: 2.
the methods used to solve these equations numerically in the subsonic- transonic region and in the supersonic region are discussed. METHOD OF SOLUTION FOR SUBSONIC-TRANSONIC REGION In the nose region of blunt bodies, equations (1) through (4) exhibit different character; namely, the equations are elliptic in the subsonic region, 5.
ELSEVIER Comput. Methods Appl. Mech. Engrg. 48 () Computer methods in applied mechanics and engineering Numerical solution for complete aircraft's subsonic-transonic- supersonic flow at high angles of attack Qin E, Guowei Yang, Fengwei Li* Northwestern Polytechnical University, Xi'an, Shaanxi, P.R.
China Received 22 November ; revised 12 April ; accepted 4 Cited by: 1. Transonic Aerodynamics of Airfoils and Wings Introduction Transonic flow occurs when there is mixed sub- and supersonic local flow in the same flowfield (typically with freestream Mach numbers from M = or to ).
Usually the supersonic region of the flow is terminated by a shock wave, allowing the flow to slow down to subsonic File Size: 2MB. NUMERICAL AND EXPERIMENTAL RESEARCH OF NEW METHODS FOR WALL INTERFERENCE REDUCTION IN WIND TUNNELS OF TRANSONIC AND LOW SUPERSONIC VELOCITIES SERGEY L.
CHERNYSHEV¹, ALEXANDER I. IVANOV², EVGENY SOV 3 AND ANASTASIA O. VOLKOVA4 Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky St., Zhukovsky, Moscow File Size: 1MB. Transonic flow fields contain a variety of interesting and unique characteristics.
Typical airfoil and swept-wing flow fields are shown in Figs. 1 and 2. The outer freestream flow is typically subsonic and elliptic in na-ture. Regions of supersonic flow usually exist on the. The flow field and aerodynamic characteristics of complete aircraft's subsonic-transonic-supersonic flow at angles of attack up to 59 ° have been successfully calculated by applying finite volume.
Abstract. The method of characteristics is a workable numerical method for the calculation of unsteady two-dimensional inviscid flow at subsonic, transonic, and supersonic speeds, and for the generation of steady flow gh the basic scheme is quite well developed, more work needs to be done, particularly in the case of subsonic free : Chong-Wei Chu, Stefan Nadir.
The Navier-Stokes, energy, and continuity equations are derived in three-dimensional, time-dependent form, and the results are applied to the treatment of one- and two-dimensional, steady and unsteady, subsonic, supersonic, and transonic flow of a perfect gas.
Departures from the perfect gas theory are discussed in chapters on laminar boundary layers, turbulent boundary layers, and real gas. Numerical Simulation of Transonic Circulation Control. Under high subsonic flow conditions, with a total blowing ratio of 3% of the mainstream, the circulation control cascade can reach the.
- The linearized theories for compressible subsonic and supersonic aerodynamics. - The nonlinear transonic small disturbance potential flow theory, including supercritical wing sections, the extended transonic area rule with lift effect, transonic lifting line and swept or oblique wings to minimize wave drag.
Unsteady flow is also briefly Format: Hardcover. The numerical methods generally showed good agreement with each other, except at some transonic Mach numbers. Both methods showed good to excellent agreement with experimental data in the high transonic and supersonic Mach regimes.
In the subsonic and low transonic regimes, agreement between numerical and experimental data was less by: This paper reports a numerical analysis of transonic flows in the axisymmetric backward-facing step main nozzle of an air-jet loom.
To obtain basic design data for the optimum main nozzle shape of an air-jet loom and to predict transonic/supersonic internal flows, a characteristic-based, upwind flux difference-splitting, compressible Navier-Stokes method is by: Prediction of drag and lift of wings from velocity and vorticity fields 3 February | The Aeronautical Journal, Vol.No.
Comparison of predicting drag methods using computational fluid dynamics in 2d/3d viscous flowCited by: The method is uniformly valid for application in the subsonic, transonic and supersonic flow regimes.
It does not rely on the introduction of additional assumptions beyond those necessary to obtain the Euler equations from the Navier-Stokes equations, nor does it make use of a time-asymptotic solution of the unsteady equations of by: 3. Kwon et al.  and Song et al.  analyzed the transonic/supersonic compressor cascade flow and the performance of transonic centrifugal compressor diffusers, respectively, using this same method.
In this study, we analyze transonic/supersonic viscous flows inside the nozzle using the inlet nozzle flow conditions from the experiments.These tests are useful both from a basic research aspect and insofar as they indicate possible methods of reducing base drag.
A careful study is made of the events which are associated with the transition, at transonic speeds, from the subsonic vortex-street r6gime to the supersonic steady-flow r6gime.Bailey and J.
Hiatt, “ Free-flight measurements of sphere drag at subsonic, transonic, supersonic, and hypersonic speeds for continuum, transition, and near-free-molecular flow conditions,” AEDC Technical Report No. AEDC-TR–, carried out free flight measurement tests of the drag of the sphere using ballistic range at the Cited by: