Author: Milton D. Van Dyke
Publisher:
ISBN:
Category :
Languages : en
Pages : 29
Book Description
Methods are studied for imporving the existing perturbation theories of axial and inclined supersonic flow past bodies of revolution. For axial flow, a second-order solution is developed using an interation procedure based upon the linearized solution. The resulting second-order problem is reduced to an equivalent first-order problem by discovery of a particular solution. The second-order supersonic flow can then be computed with slight modification of the Karman-Moore procedure. For inclined flow, no particular solution of the second-order equation has been discovered. The second-order solution is derived for a cone, and agrees well with the exact solution. The slender-body series expansion of the second-order solution is found to cause large inaccuracies in both the axial and inclined flows. The conclusion that first-order theory predicts the inclined flow no better than slender-body theory is shown to be erroneous. Non-linearity in lift is shown to result primarily from viscous separation of the crossflow along the after portions of the body. (Author).
First-order and Second-order Theory of Supersonic Flow Past Bodies of Revolution
Author: Milton D. Van Dyke
Publisher:
ISBN:
Category :
Languages : en
Pages : 29
Book Description
Methods are studied for imporving the existing perturbation theories of axial and inclined supersonic flow past bodies of revolution. For axial flow, a second-order solution is developed using an interation procedure based upon the linearized solution. The resulting second-order problem is reduced to an equivalent first-order problem by discovery of a particular solution. The second-order supersonic flow can then be computed with slight modification of the Karman-Moore procedure. For inclined flow, no particular solution of the second-order equation has been discovered. The second-order solution is derived for a cone, and agrees well with the exact solution. The slender-body series expansion of the second-order solution is found to cause large inaccuracies in both the axial and inclined flows. The conclusion that first-order theory predicts the inclined flow no better than slender-body theory is shown to be erroneous. Non-linearity in lift is shown to result primarily from viscous separation of the crossflow along the after portions of the body. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 29
Book Description
Methods are studied for imporving the existing perturbation theories of axial and inclined supersonic flow past bodies of revolution. For axial flow, a second-order solution is developed using an interation procedure based upon the linearized solution. The resulting second-order problem is reduced to an equivalent first-order problem by discovery of a particular solution. The second-order supersonic flow can then be computed with slight modification of the Karman-Moore procedure. For inclined flow, no particular solution of the second-order equation has been discovered. The second-order solution is derived for a cone, and agrees well with the exact solution. The slender-body series expansion of the second-order solution is found to cause large inaccuracies in both the axial and inclined flows. The conclusion that first-order theory predicts the inclined flow no better than slender-body theory is shown to be erroneous. Non-linearity in lift is shown to result primarily from viscous separation of the crossflow along the after portions of the body. (Author).
Second Order Theory for Unsteady Super-sonic Flow Past Slender, Pointed Bodies of Revolution
Author: James Dewey Revell
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 180
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 180
Book Description
Wing Theory in Supersonic Flow
Author: Elie Carafoli
Publisher: Elsevier
ISBN: 1483160270
Category : Technology & Engineering
Languages : en
Pages : 611
Book Description
Division II: Aerodynamics, Volume 7: Wing Theory in Supersonic Flow examines the cases of isolated simple wings, wings with vertical plane tail, cruciform wings, and simple or cruciform wings fitted with a body. This book presents the method for the actual calculation of isolated wings or of more complex system. Organized into 12 chapters, this volume starts with an overview of the basic equations in the mechanics of inviscid fluids. This text then presents a unified theory that is established for angularly shaped wings in supersonic flow. Other chapters consider the method for calculating the characteristics of drag, lift, and moments for various shapes of the trailing edge line. This book discusses as well the wings of ordinary shapes, delta wings, yawed wings, polygonal wings, trapezoid wings, and arrow-head or swept-back wings. The final chapter deals with a delta wing with a central fusiform body. This book is a valuable resource for teachers, students, and specialists engaged in modern aerodynamics.
Publisher: Elsevier
ISBN: 1483160270
Category : Technology & Engineering
Languages : en
Pages : 611
Book Description
Division II: Aerodynamics, Volume 7: Wing Theory in Supersonic Flow examines the cases of isolated simple wings, wings with vertical plane tail, cruciform wings, and simple or cruciform wings fitted with a body. This book presents the method for the actual calculation of isolated wings or of more complex system. Organized into 12 chapters, this volume starts with an overview of the basic equations in the mechanics of inviscid fluids. This text then presents a unified theory that is established for angularly shaped wings in supersonic flow. Other chapters consider the method for calculating the characteristics of drag, lift, and moments for various shapes of the trailing edge line. This book discusses as well the wings of ordinary shapes, delta wings, yawed wings, polygonal wings, trapezoid wings, and arrow-head or swept-back wings. The final chapter deals with a delta wing with a central fusiform body. This book is a valuable resource for teachers, students, and specialists engaged in modern aerodynamics.
Reverse-flow Integral Methods for Second-order Supersonic Flow Theory
Author: Joseph Henry Clarke
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
Book Description
A general reverse-flow relation is obtained within the framework of second-order (in surface deflection) supersonic flow theory. From this it is shown that the second-order increment in the drag of an arbitrary quasicylindrical body can be expressed as surface and volume integrals of the first-order solutions corresponding to forward and reverse flow past the body. Analogous results are obtained for second-order transverse forces and moments on an arbitrary quasiplanar wing, except the first-order reverse flow must correspond to certain zero-thickness wings. Other similar results are possible. Thus, second order aerodynamic forces on bodies may be obtained from first-order solutions by quadrature. It is also shown that the reverse-flow integral relation can yield the pressure distribution on the surface by inversion of an integral equation constructed therefrom. It is thought that these results should be particularly useful for the Mach number range between that of linearized theory and that of full hypersonic small-disturbance theory. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
Book Description
A general reverse-flow relation is obtained within the framework of second-order (in surface deflection) supersonic flow theory. From this it is shown that the second-order increment in the drag of an arbitrary quasicylindrical body can be expressed as surface and volume integrals of the first-order solutions corresponding to forward and reverse flow past the body. Analogous results are obtained for second-order transverse forces and moments on an arbitrary quasiplanar wing, except the first-order reverse flow must correspond to certain zero-thickness wings. Other similar results are possible. Thus, second order aerodynamic forces on bodies may be obtained from first-order solutions by quadrature. It is also shown that the reverse-flow integral relation can yield the pressure distribution on the surface by inversion of an integral equation constructed therefrom. It is thought that these results should be particularly useful for the Mach number range between that of linearized theory and that of full hypersonic small-disturbance theory. (Author).
Second-order Slender-body Theory
Author: Milton Van Dyke
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
Slender-body theory for subsonic and supersonic flow past bodies of revolution is extended to a second approximation. Methods are developed for handling the difficulties that arise at round ends. Comparison is made with experiment and with other theories for several simple shapes.
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Book Description
Slender-body theory for subsonic and supersonic flow past bodies of revolution is extended to a second approximation. Methods are developed for handling the difficulties that arise at round ends. Comparison is made with experiment and with other theories for several simple shapes.
Handbook of Supersonic Aerodynamics
Author: Johns Hopkins University. Applied Physics Laboratory
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 372
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 372
Book Description
Comparison of High-speed Operating Characteristics of Size 215 Cylindrical-roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig
Author: Arthur W. Goldstein
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 236
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 236
Book Description
Handbook of Supersonic Aerodynamics
Author: D. Adamson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 366
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 366
Book Description
Second-order Wave Structure in Supersonic Flows
Author: David A. Caughey
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 98
Book Description
This report investigates the mathematical analysis of wave structure in supersonic flow.
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 98
Book Description
This report investigates the mathematical analysis of wave structure in supersonic flow.