Author: C. W. Chiang
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
Book Description
Analysis of Supersonic Conical Flows
Author: C. W. Chiang
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
Book Description
An Analysis of Supersonic Flow Phenomena in Conical Nozzles by a Method of Characteristics
Author: Linwood B. Callis
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 60
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 60
Book Description
A Study of Supersonic Conical Flow
Author: Masahiro Kurosaki
Publisher:
ISBN:
Category :
Languages : en
Pages : 51
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 51
Book Description
Supersonic Flow Around Right Circular Cones, Tables for Zero Angle of Attack
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 882
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 882
Book Description
Supersonic Conical Flow
Author: Stephen H. Maslen
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
A numerical method is described for the solution of the nonlinear equations for supersonic conical flow. The procedure is a combination of the method of characteristics and the relaxation process. A method for calculating the position of the shock is inherent in the analysis. The method presented is applicable to any conical flow and a solution for the flow about a triangular wing with supersonic leading edges is included as an illustration.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
A numerical method is described for the solution of the nonlinear equations for supersonic conical flow. The procedure is a combination of the method of characteristics and the relaxation process. A method for calculating the position of the shock is inherent in the analysis. The method presented is applicable to any conical flow and a solution for the flow about a triangular wing with supersonic leading edges is included as an illustration.
Analysis of the Linearized Supersonic Flow about Pointed Bodies of Revolution by the Method of Characteristics
Author: Alan D. Sherer
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
Book Description
Analysis of the Three-dimensional Compressible Turbulent Boundary Layer on a Sharp Cone at Incidence in Supersonic and Hypersonic Flow
Author: John C. Adams
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 98
Book Description
An analytical approach toward numerical calculation of the three-dimensional turbulent boundary layer on a sharp cone at incidence under supersonic and hypersonic flow conditions is presented. The theoretical model is based on implicit finite-difference integration of the governing three-dimensional turbulent boundary-layer equations in conjunction with a three-dimensional scalar eddy-viscosity model of turbulence. Comparison is made of present theory with detailed experimental measurements of the three-dimensional turbulent boundary-layer structure (velocity and temperature profiles), the surface streamline direction (obtained via an oil-flow technique) and surface heat-transfer rate.
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 98
Book Description
An analytical approach toward numerical calculation of the three-dimensional turbulent boundary layer on a sharp cone at incidence under supersonic and hypersonic flow conditions is presented. The theoretical model is based on implicit finite-difference integration of the governing three-dimensional turbulent boundary-layer equations in conjunction with a three-dimensional scalar eddy-viscosity model of turbulence. Comparison is made of present theory with detailed experimental measurements of the three-dimensional turbulent boundary-layer structure (velocity and temperature profiles), the surface streamline direction (obtained via an oil-flow technique) and surface heat-transfer rate.
Generalized Conical-flow Fields in Supersonic Wing Theory
Author: Harvard Lomax
Publisher:
ISBN:
Category : Aiprlanes
Languages : en
Pages : 45
Book Description
Linearized, compressible-flow analysis is applied to the study of quasi-conical supersonic wing theory. Single-integral equations are derived which relate either the loading to the shape of a lifting surface or the thickness of a symmetrical wing to the pressure distribution for triangular wings to the pressure distribution for triangular wings with subsonic leading edges. The forms of these equations and their inversions are simplified thorugh the introduction of the finite part and the generalized part of an integral. Applications to the theory, in the lifting case, include previously known results. In the non-lifing case, it is shown that for a specified pressure distribution the theory does not always predict a unique thickness distribution. This is demonstrated for a triangular plan form having a constant pressure gradient in the stream direction.
Publisher:
ISBN:
Category : Aiprlanes
Languages : en
Pages : 45
Book Description
Linearized, compressible-flow analysis is applied to the study of quasi-conical supersonic wing theory. Single-integral equations are derived which relate either the loading to the shape of a lifting surface or the thickness of a symmetrical wing to the pressure distribution for triangular wings to the pressure distribution for triangular wings with subsonic leading edges. The forms of these equations and their inversions are simplified thorugh the introduction of the finite part and the generalized part of an integral. Applications to the theory, in the lifting case, include previously known results. In the non-lifing case, it is shown that for a specified pressure distribution the theory does not always predict a unique thickness distribution. This is demonstrated for a triangular plan form having a constant pressure gradient in the stream direction.
A Study of Flow about Objects Traveling at High Supersonic Speeds
Author: Alfred John Eggers (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 298
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 298
Book Description
Laminar Boundary Layer on a Circular Cone in Supersonic Flow at a Small Angle of Attack
Author: Franklin K. Moore
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 710
Book Description
The laminar boundary layer on a circular cone at angle of attack to a supersonic stream is discussed. A perturbation analysis was made to show the influence of a small angle of attack on such boundary layer quantities as skin friction, boundary-layer thickness, viscous lift, drag, and pitching moment.
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 710
Book Description
The laminar boundary layer on a circular cone at angle of attack to a supersonic stream is discussed. A perturbation analysis was made to show the influence of a small angle of attack on such boundary layer quantities as skin friction, boundary-layer thickness, viscous lift, drag, and pitching moment.