Duck, Peter W.
Overview
Works:  32 works in 102 publications in 1 language and 1,621 library holdings 

Genres:  Conference papers and proceedings 
Roles:  Author, Editor, Other, ed 
Publication Timeline
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Most widely held works by
Peter W Duck
The unsteady laminar boundary layer on an axisymmetric body subject to small amplitude fluctuations in the freestream velocity by
Peter W Duck(
Book
)
3 editions published in 1991 in English and held by 146 WorldCat member libraries worldwide
3 editions published in 1991 in English and held by 146 WorldCat member libraries worldwide
The inviscid stability of supersonic flow past a sharp cone by
Peter W Duck(
Book
)
5 editions published in 1990 in English and held by 140 WorldCat member libraries worldwide
In this paper we consider the laminar boundary layer which forms on a sharp cone in a supersonic freestream, where lateral curvature plays a key role in the physics of the problem. This flow is then analysed from the point of view of linear, temporal, inviscid stability. Indeed, the basic, nonaxisymmetric disturbance equations are derived for general flows of this class, and a so called triply generalised inflexion condition is found for the existence of subsonic neutral modes in instability. This condition is analogous to the well known generalised inflexion condition found in planar flows, although in the present case the condition depends on both axial and aximuthal wavenumbers. Extensive numerical results are presented for the stability problem at a freestream Mach number of 3.8, for a range of streamwise locations. These results reveal that a new mode of instability may occur, perculiar to flows of this type involving lateral curvature. Additionally, asymptotic analyses valid close to the tip of the cone/far downstream of the cone are presented, and these give a partial (asymptotic) description of this additional mode of instability. (Author) (KR)
5 editions published in 1990 in English and held by 140 WorldCat member libraries worldwide
In this paper we consider the laminar boundary layer which forms on a sharp cone in a supersonic freestream, where lateral curvature plays a key role in the physics of the problem. This flow is then analysed from the point of view of linear, temporal, inviscid stability. Indeed, the basic, nonaxisymmetric disturbance equations are derived for general flows of this class, and a so called triply generalised inflexion condition is found for the existence of subsonic neutral modes in instability. This condition is analogous to the well known generalised inflexion condition found in planar flows, although in the present case the condition depends on both axial and aximuthal wavenumbers. Extensive numerical results are presented for the stability problem at a freestream Mach number of 3.8, for a range of streamwise locations. These results reveal that a new mode of instability may occur, perculiar to flows of this type involving lateral curvature. Additionally, asymptotic analyses valid close to the tip of the cone/far downstream of the cone are presented, and these give a partial (asymptotic) description of this additional mode of instability. (Author) (KR)
Unsteady threedimensional marginal separation, including breakdown by
Peter W Duck(
Book
)
1 edition published in 1990 in English and held by 130 WorldCat member libraries worldwide
1 edition published in 1990 in English and held by 130 WorldCat member libraries worldwide
The threedimensional flow past a rapidly rotating circular cylinder by
James P Denier(
Book
)
6 editions published in 1993 in English and held by 94 WorldCat member libraries worldwide
The high Reynolds number (Re) flow past a rapidly rotating circular cylinder is investigated. The rotation rate of the cylinder is allowed to vary (slightly) along the axis of the cylinder, thereby provoking threedimensional flow disturbances, which are shown to involve relatively massive (O(Re)) velocity perturbations to the flow away from the cylinder surface. Additionally, three integral conditions, analogous to the single condition determine in two dimensions by Batchelor (1), are derived, based on the condition of periodicity in the azimuthal direction. Rotating cylinder, Threedimensional flow
6 editions published in 1993 in English and held by 94 WorldCat member libraries worldwide
The high Reynolds number (Re) flow past a rapidly rotating circular cylinder is investigated. The rotation rate of the cylinder is allowed to vary (slightly) along the axis of the cylinder, thereby provoking threedimensional flow disturbances, which are shown to involve relatively massive (O(Re)) velocity perturbations to the flow away from the cylinder surface. Additionally, three integral conditions, analogous to the single condition determine in two dimensions by Batchelor (1), are derived, based on the condition of periodicity in the azimuthal direction. Rotating cylinder, Threedimensional flow
Threedimensional marginal separation by
Peter W Duck(
Book
)
3 editions published between 1988 and 1989 in English and Undetermined and held by 94 WorldCat member libraries worldwide
3 editions published between 1988 and 1989 in English and Undetermined and held by 94 WorldCat member libraries worldwide
On the interactions between the shock wave attached to a wedge and freestream disturbances by
Peter W Duck(
Book
)
6 editions published in 1993 in English and held by 92 WorldCat member libraries worldwide
We present a study of the interaction of small amplitude, unsteady, freestream disturbances with a shock wave induced by a wedge in supersonic flow. These disturbances may be acoustic waves, vorticity waves, or entropy waves (or indeed a combination of all three). Their interactions then generate behind the shock disturbances of all three classes, an aspect that is investigated in some detail, our motivation here being to investigate possible mechanisms for boundarylayer receptivity, caused through the amplification and modification of freestream turbulence through shockbody coupling. Also, the possibility of enhanced mixing owing to additional vorticity produced by the shockbody coupling is investigated
6 editions published in 1993 in English and held by 92 WorldCat member libraries worldwide
We present a study of the interaction of small amplitude, unsteady, freestream disturbances with a shock wave induced by a wedge in supersonic flow. These disturbances may be acoustic waves, vorticity waves, or entropy waves (or indeed a combination of all three). Their interactions then generate behind the shock disturbances of all three classes, an aspect that is investigated in some detail, our motivation here being to investigate possible mechanisms for boundarylayer receptivity, caused through the amplification and modification of freestream turbulence through shockbody coupling. Also, the possibility of enhanced mixing owing to additional vorticity produced by the shockbody coupling is investigated
The response of a laminar boundary layer in supersonic flow to small amplitude progressive waves by
Peter W Duck(
Book
)
1 edition published in 1989 in English and held by 91 WorldCat member libraries worldwide
1 edition published in 1989 in English and held by 91 WorldCat member libraries worldwide
The stability of a trailingline vortex in compressible flow by
Jillian A. K Stott(
Book
)
7 editions published in 1992 in English and held by 90 WorldCat member libraries worldwide
We consider the inviscid stability of the Batchelor (1964) vortex in a compressible flow. The problem is tackled numerically and also asymptotically, in the limit of large (azimuthal and streamwise) wavenumbers, together with large Mach numbers. The nature of the solution passes through different regimes as the Mach number increases, relative to the wavenumbers. At very high wavenumbers and Mach numbers, the mode which is present in the incompressible case ceases to be unstable, whilst new 'centre mode' forms, whose stability characteristics are determined primarily by conditions close to the vortex axis. We find that generally the flow becomes less unstable as the Mach number increases, and that the regime of instability appears generally confined to disturbances in a direction counter to the direction of the rotation of the swirl of the vortex. Throughout the paper comparison is made between our numerical results and results obtained from the various asymptotic theories ... Inviscid, Vortex, Stability
7 editions published in 1992 in English and held by 90 WorldCat member libraries worldwide
We consider the inviscid stability of the Batchelor (1964) vortex in a compressible flow. The problem is tackled numerically and also asymptotically, in the limit of large (azimuthal and streamwise) wavenumbers, together with large Mach numbers. The nature of the solution passes through different regimes as the Mach number increases, relative to the wavenumbers. At very high wavenumbers and Mach numbers, the mode which is present in the incompressible case ceases to be unstable, whilst new 'centre mode' forms, whose stability characteristics are determined primarily by conditions close to the vortex axis. We find that generally the flow becomes less unstable as the Mach number increases, and that the regime of instability appears generally confined to disturbances in a direction counter to the direction of the rotation of the swirl of the vortex. Throughout the paper comparison is made between our numerical results and results obtained from the various asymptotic theories ... Inviscid, Vortex, Stability
Nonaxisymmetric viscous lower branch modes in axisymmetric supersonic flows by
Peter W Duck(
Book
)
5 editions published in 1988 in English and held by 86 WorldCat member libraries worldwide
5 editions published in 1988 in English and held by 86 WorldCat member libraries worldwide
On the effects of viscosity on the stability of a trailingline vortex by
P. W Duck(
Book
)
6 editions published in 1991 in English and held by 85 WorldCat member libraries worldwide
The linear stability of the Batchelor (1960) vortex is investigated. Particular emphasis is placed on modes found recently in a numerical study by Khorrami (1991). These modes have a number of features very distinct from those found previously for this vortex, including (i) exhibiting small growth rates at large Reynolds numbers and (ii) susceptibility to destabilisation by viscosity. In this paper these modes are described using asymptotic techniques, producing results which compare favourably with fully numerical results at large Reynolds numbers
6 editions published in 1991 in English and held by 85 WorldCat member libraries worldwide
The linear stability of the Batchelor (1960) vortex is investigated. Particular emphasis is placed on modes found recently in a numerical study by Khorrami (1991). These modes have a number of features very distinct from those found previously for this vortex, including (i) exhibiting small growth rates at large Reynolds numbers and (ii) susceptibility to destabilisation by viscosity. In this paper these modes are described using asymptotic techniques, producing results which compare favourably with fully numerical results at large Reynolds numbers
The effect of threedimensional freestream disturbances on the supersonic flow past a wedge : NASA contract no. NAS119480 by
Peter W Duck(
Book
)
6 editions published in 1997 in English and held by 83 WorldCat member libraries worldwide
The interaction between a shock wave (attached to a wedge) and small amplitude, threedimensional disturbances of a uniform, supersonic, freestream flow are investigated. The paper extends the twodimensional study of Duck et al(1), through the use of vector potentials, which render the problem tractable by the same techniques as in the twodimensional case, in particular by expansion of the solution by means of a FourierBessel series, in appropriately chosen coordinates. Results are presented for specific classes of freestream disturbances, and the study shows conclusively that the shock is stable to all classes of disturbances (i.e. time periodic perturbations to the shock do not grow downstream), provided the flow downstream of the shock is supersonic (loosely corresponding to the weak shock solution). This is shown from our numerical results and also by asymptotic analysis of the FourierBessel series, valid far downstream of the shock
6 editions published in 1997 in English and held by 83 WorldCat member libraries worldwide
The interaction between a shock wave (attached to a wedge) and small amplitude, threedimensional disturbances of a uniform, supersonic, freestream flow are investigated. The paper extends the twodimensional study of Duck et al(1), through the use of vector potentials, which render the problem tractable by the same techniques as in the twodimensional case, in particular by expansion of the solution by means of a FourierBessel series, in appropriately chosen coordinates. Results are presented for specific classes of freestream disturbances, and the study shows conclusively that the shock is stable to all classes of disturbances (i.e. time periodic perturbations to the shock do not grow downstream), provided the flow downstream of the shock is supersonic (loosely corresponding to the weak shock solution). This is shown from our numerical results and also by asymptotic analysis of the FourierBessel series, valid far downstream of the shock
The inviscid axisymmetric stability of the supersonic flow along a circular cylinder by
Peter W Duck(
Book
)
4 editions published in 1989 in English and held by 81 WorldCat member libraries worldwide
4 editions published in 1989 in English and held by 81 WorldCat member libraries worldwide
On the linear stability of compressible plane couette flow by
P. W Duck(
Book
)
5 editions published in 1991 in English and held by 80 WorldCat member libraries worldwide
The linear stability of compressible plane Couette flow is investigated. The correct and proper basic velocity and temperature distributions are perturbed by a small amplitude normal mode disturbance. The full small amplitude disturbance equations are solved numerically at finite Reynolds numbers, and the inviscid limit of these equations is then investigated in some detail. It is found that instability can occur, although the stability characteristics of the flow are quite different from unbounded flows. The effects of viscosity are also calculated, asymptotically, and shown to have a stabilizing role in all the cases investigated. Exceptional regimes to the problem occur when the wavespeed of the disturbances approaches the velocity of either of the walls, and these regimes are also analyzed in some details. Finally, the effect of imposing radiationtype boundary conditions on the upper (moving) wall (in place of impermeability) is investigated, and shown to yield results common to both bounded and unbounded flows
5 editions published in 1991 in English and held by 80 WorldCat member libraries worldwide
The linear stability of compressible plane Couette flow is investigated. The correct and proper basic velocity and temperature distributions are perturbed by a small amplitude normal mode disturbance. The full small amplitude disturbance equations are solved numerically at finite Reynolds numbers, and the inviscid limit of these equations is then investigated in some detail. It is found that instability can occur, although the stability characteristics of the flow are quite different from unbounded flows. The effects of viscosity are also calculated, asymptotically, and shown to have a stabilizing role in all the cases investigated. Exceptional regimes to the problem occur when the wavespeed of the disturbances approaches the velocity of either of the walls, and these regimes are also analyzed in some details. Finally, the effect of imposing radiationtype boundary conditions on the upper (moving) wall (in place of impermeability) is investigated, and shown to yield results common to both bounded and unbounded flows
The effects of viscosity on the stability of a trailingline vortex in compressible flow by
Jillian A. K Stott(
Book
)
4 editions published in 1994 in English and held by 80 WorldCat member libraries worldwide
4 editions published in 1994 in English and held by 80 WorldCat member libraries worldwide
On the interaction of TollmienSchlichting waves in axisymmetric supersonic flows by
P. W Duck(
Book
)
3 editions published in 1988 in English and held by 77 WorldCat member libraries worldwide
3 editions published in 1988 in English and held by 77 WorldCat member libraries worldwide
IUTAM Symposium on Nonlinear Instability and Transition in ThreeDimensional Boundary Layers : proceedings of the IUTAM Symposium
held in Manchester, UK, 1720 July 1995 by IUTAM Symposium on Nonlinear Instability and Transition in ThreeDimensional Boundary Layers(
Book
)
7 editions published in 1996 in English and held by 76 WorldCat member libraries worldwide
7 editions published in 1996 in English and held by 76 WorldCat member libraries worldwide
IUTAM Symposium on Nonlinear Instability and Transition in ThreeDimensional Boundary Layers : Proceedings of the IUTAM Symposium
held in Manchester, U.K., 1720 July 1995 by
Peter W Duck(
)
1 edition published in 1996 in English and held by 43 WorldCat member libraries worldwide
Most fluid flows of practical importance are fully threedimensional, so the nonlinear instability properties of threedimensional flows are of particular interest. In some cases the threedimensionality may have been caused by a finite amplitude disturbance whilst, more usually, the unperturbed state is threedimensional. Practical applications where transition is thought to be associated with nonlinearity in a three dimensional flow arise, for example, in aerodynamics (swept wings, engine nacelles, etc.), turbines and aortic blood flow. Here inviscid 'crossflow' disturbances as well as TollmienSchlichting and Görtler vortices can all occur simultaneously and their mutual nonlinear behaviour must be understood if transition is to be predicted. The nonlinear interactions are so complex that usually fully numerical or combined asymptotic/numerical methods must be used. <br/> Moreover, in view of the complexity of the instability processes, there is also a growing need for detailed and accurate experimental information. Carefully conducted tests allow us to identify those elements of a particular problem which are dominant. This assists in both the formulation of a relevant theoretical problem and the subsequent physical validation of predictions. It should be noted that the demands made upon the skills of the experimentalist are high and that the tests can be extremely sophisticated  often making use of the latest developments in flow diagnostic techniques, automated high speed data gathering, data analysis, fast processing and presentation
1 edition published in 1996 in English and held by 43 WorldCat member libraries worldwide
Most fluid flows of practical importance are fully threedimensional, so the nonlinear instability properties of threedimensional flows are of particular interest. In some cases the threedimensionality may have been caused by a finite amplitude disturbance whilst, more usually, the unperturbed state is threedimensional. Practical applications where transition is thought to be associated with nonlinearity in a three dimensional flow arise, for example, in aerodynamics (swept wings, engine nacelles, etc.), turbines and aortic blood flow. Here inviscid 'crossflow' disturbances as well as TollmienSchlichting and Görtler vortices can all occur simultaneously and their mutual nonlinear behaviour must be understood if transition is to be predicted. The nonlinear interactions are so complex that usually fully numerical or combined asymptotic/numerical methods must be used. <br/> Moreover, in view of the complexity of the instability processes, there is also a growing need for detailed and accurate experimental information. Carefully conducted tests allow us to identify those elements of a particular problem which are dominant. This assists in both the formulation of a relevant theoretical problem and the subsequent physical validation of predictions. It should be noted that the demands made upon the skills of the experimentalist are high and that the tests can be extremely sophisticated  often making use of the latest developments in flow diagnostic techniques, automated high speed data gathering, data analysis, fast processing and presentation
The numerical calculation of steady inviscid supercritical flow past ellipsoids without circulation by
Peter W Duck(
Book
)
4 editions published between 1975 and 1977 in English and held by 10 WorldCat member libraries worldwide
The previous work of the author in which the subcritical flow past ellipsoids was calculated is extended to supercritical flows. The same ellipsoidal coordinate system is used, the bodysurface boundarycondition is then applied exactly (in the numerical sense). By means of a transformation of one of the coordinates, the infinite flow field is brought into a finite space for the calculation. The complete continuity equation is approximated by the usual central differencing in the elliptic (subcritical) regions, whilst in the hyperbolic (supercritical) regions, the combination of central and noncentral differencing as suggested by Albone and Jameson is used, in order to model the absence of upstream propagation of disturbances. Although shock waves appear in the calculations their shape and position is only approximately determined (as e.g. in transonic small perturbation theory) since the difference scheme only ensures continuity of the potential across the shock, the RankineHugoniot equations not being satisfied. A number of results is presented, for flows aligned along the major and second axes, and also yawed relative to these two axes. (Author)
4 editions published between 1975 and 1977 in English and held by 10 WorldCat member libraries worldwide
The previous work of the author in which the subcritical flow past ellipsoids was calculated is extended to supercritical flows. The same ellipsoidal coordinate system is used, the bodysurface boundarycondition is then applied exactly (in the numerical sense). By means of a transformation of one of the coordinates, the infinite flow field is brought into a finite space for the calculation. The complete continuity equation is approximated by the usual central differencing in the elliptic (subcritical) regions, whilst in the hyperbolic (supercritical) regions, the combination of central and noncentral differencing as suggested by Albone and Jameson is used, in order to model the absence of upstream propagation of disturbances. Although shock waves appear in the calculations their shape and position is only approximately determined (as e.g. in transonic small perturbation theory) since the difference scheme only ensures continuity of the potential across the shock, the RankineHugoniot equations not being satisfied. A number of results is presented, for flows aligned along the major and second axes, and also yawed relative to these two axes. (Author)
The numerical calculation of subcritical steady potential flow around an unyawed ellipsoid by
Peter W Duck(
Book
)
3 editions published between 1975 and 1977 in English and held by 8 WorldCat member libraries worldwide
The problem of a subcritical, potential, steady, threedimensional flow past an unyawed ellipsoid is considered, using ellipsoidal coordinates. The full equations of motion and the exact body surface boundary condition are used throughout. Further, by means of a simple transformation the entire flow field is taken into the computation. A finite difference method, followed by an iterative process is used for the solution of the flow equations. Mach number distributions are given for a number of examples, for the freestream flow aligned along either the major axis, or the second major axis of the ellipsoid. (Author)
3 editions published between 1975 and 1977 in English and held by 8 WorldCat member libraries worldwide
The problem of a subcritical, potential, steady, threedimensional flow past an unyawed ellipsoid is considered, using ellipsoidal coordinates. The full equations of motion and the exact body surface boundary condition are used throughout. Further, by means of a simple transformation the entire flow field is taken into the computation. A finite difference method, followed by an iterative process is used for the solution of the flow equations. Mach number distributions are given for a number of examples, for the freestream flow aligned along either the major axis, or the second major axis of the ellipsoid. (Author)
The inviscid stability of supersonic flow past heated or cooled axisymmetric bodies by
Institute for Computer Applications in Science and Engineering(
Book
)
5 editions published in 1990 in English and held by 8 WorldCat member libraries worldwide
The inviscid, linear, nonaxisymmetric, temporal stability of the boundary layer associated with the supersonic flow past axisymmetric bodies (with particular emphasis on long thin, straight circular cylinders), subject to heated or cooled wall conditions is investigated. The eigenvalue problem is computed in some detail for a particular Mach number or 3.8, revealing that the effect of curvature and the choice of wall conditions both have a significant effect on the stability of the flow. Both the asymptotic, large azimuthal wavenumber solution and the asymptotic, far downstream solution are obtained for the stability analysis and compared with numerical results. Additionally, asymptotic analyses valid for large radii of curvature with cooledheated wall conditions, are presented. Important differences exist between the wall temperature conditions imposed in this paper and the adabatic wall conditions considered previously
5 editions published in 1990 in English and held by 8 WorldCat member libraries worldwide
The inviscid, linear, nonaxisymmetric, temporal stability of the boundary layer associated with the supersonic flow past axisymmetric bodies (with particular emphasis on long thin, straight circular cylinders), subject to heated or cooled wall conditions is investigated. The eigenvalue problem is computed in some detail for a particular Mach number or 3.8, revealing that the effect of curvature and the choice of wall conditions both have a significant effect on the stability of the flow. Both the asymptotic, large azimuthal wavenumber solution and the asymptotic, far downstream solution are obtained for the stability analysis and compared with numerical results. Additionally, asymptotic analyses valid for large radii of curvature with cooledheated wall conditions, are presented. Important differences exist between the wall temperature conditions imposed in this paper and the adabatic wall conditions considered previously
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Related Identities
 Institute for Computer Applications in Science and Engineering
 Langley Research Center
 Hussaini, M. Yousuff
 United States National Aeronautics and Space Administration
 Lasseigne, D. G. (David Glenn) 1959
 Stott, Jillian A. K. Author
 Shaw, Stephen J. Author
 Lewis Research Center Institute for Computational Mechanics in Propulsion
 Hall, Philip Other
 Denier, James P. Author
Associated Subjects
Aerodynamics Aerodynamics, Supersonic Boundary layer Boundary layerMathematical models Cylinders Dimensional analysis Flows (Differentiable dynamical systems) Fluid dynamics Fluid mechanics Fourier series Laminar boundary layer Mach number Mathematical models Nonlinear theories Reynolds number Shock waves Stability Turbulence Viscosity Viscous flow Vortexmotion Wedges Whirlwinds