Author: Guion Stewart Bluford (Jr.)
Publisher:
ISBN:
Category :
Languages : en
Pages : 233
Book Description
A numerical technique was used to compute the supersonic and hypersonic, viscous flow fields around thin planar delta wings. These solutions were obtained by solving the Navier-Stokes equations subject to a conical approximation. The integration technique used was the MacCormack finite-difference scheme. Solutions were obtained for the upper-only, lower-only, and total flow fields around delta wings with supersonic leading edges. These solutions span a Mach number range of 2.94 to 10.17, a local Reynolds number range of 334,500 to 5,000,000, and various angles of attack from -15 to +15 deg. A stability criteria was developed and used which accounted for both the viscous and inviscid flow regions. Good agreement was obtained between the numerical results and experimental flow field data. The shock-induced vortex within the viscous region and the hypersonic viscous bubble on top of the boundary layer were computed, for the first time. A unique examination was made of the vortical singularities in the conical cross-flow plane of the delta wing. This investigation demonstrated the feasibility of applying the conical approximation to the Navier-Stokes equations in order to solve flow fields around thin delta wings.
A Numerical Solution of Supersonic and Hypersonic Viscous Flow Fields Around Thin Planar Delta Wings
Author: Guion Stewart Bluford (Jr.)
Publisher:
ISBN:
Category :
Languages : en
Pages : 233
Book Description
A numerical technique was used to compute the supersonic and hypersonic, viscous flow fields around thin planar delta wings. These solutions were obtained by solving the Navier-Stokes equations subject to a conical approximation. The integration technique used was the MacCormack finite-difference scheme. Solutions were obtained for the upper-only, lower-only, and total flow fields around delta wings with supersonic leading edges. These solutions span a Mach number range of 2.94 to 10.17, a local Reynolds number range of 334,500 to 5,000,000, and various angles of attack from -15 to +15 deg. A stability criteria was developed and used which accounted for both the viscous and inviscid flow regions. Good agreement was obtained between the numerical results and experimental flow field data. The shock-induced vortex within the viscous region and the hypersonic viscous bubble on top of the boundary layer were computed, for the first time. A unique examination was made of the vortical singularities in the conical cross-flow plane of the delta wing. This investigation demonstrated the feasibility of applying the conical approximation to the Navier-Stokes equations in order to solve flow fields around thin delta wings.
Publisher:
ISBN:
Category :
Languages : en
Pages : 233
Book Description
A numerical technique was used to compute the supersonic and hypersonic, viscous flow fields around thin planar delta wings. These solutions were obtained by solving the Navier-Stokes equations subject to a conical approximation. The integration technique used was the MacCormack finite-difference scheme. Solutions were obtained for the upper-only, lower-only, and total flow fields around delta wings with supersonic leading edges. These solutions span a Mach number range of 2.94 to 10.17, a local Reynolds number range of 334,500 to 5,000,000, and various angles of attack from -15 to +15 deg. A stability criteria was developed and used which accounted for both the viscous and inviscid flow regions. Good agreement was obtained between the numerical results and experimental flow field data. The shock-induced vortex within the viscous region and the hypersonic viscous bubble on top of the boundary layer were computed, for the first time. A unique examination was made of the vortical singularities in the conical cross-flow plane of the delta wing. This investigation demonstrated the feasibility of applying the conical approximation to the Navier-Stokes equations in order to solve flow fields around thin delta wings.
A Numerical Solution of Supersonic and Hypersonic Viscous Flow Fields Around Thin Planar Delta Wings
Author: Guion S. Bluford
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 211
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 211
Book Description
Calculation of Supersonic Viscous Flow Over Delta Wings with Sharp Subsonic Leading Edges
Author: Y. C. Vigneron
Publisher:
ISBN:
Category :
Languages : en
Pages : 86
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 86
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 994
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 994
Book Description
Leeward Flow Over Delta Wings at Supersonic Speeds
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 54
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 54
Book Description
Numerical Solution of Supersonic Viscous Flow Over Blunt Delta Wings
Author:
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1148
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1148
Book Description
On the Hypersonic Flow Over a Delta Wing with Very Supersonic Leading Edges
Author: Norman D. Malmuth
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 60
Book Description
For the case of very supersonic leading edges, the inviscid hypersonic flow over the windward side of a symmetrical flat-plate delta wing at incidence is analyzed. The limit selected is that the incidence is of higher order than the aspect ratio as the incidence tends to zero at infinite Mach number. In this framework, the flow regions consist of a two-dimensional domain adjacent to the leading edges and a central conefield. The flow quantities in the central region represent small linear, rotational perturbations about the zero sweep flow. A Riemann-Poincare boundary value problem for the pressure perturbation is formulated. An additional condition involving the sidewash at the shock is found to be required to resolve the indeterminacy of the foregoing boundary value problem. Series solutions and numerical results are presented for the shock shape and the pressure. The behavior of the latter quantity is found to be similar to that given by the irrotational linear solution for the supersonic leading edge case. Finally, the relationship between the present application and others involving diffraction problems and corner flows is indicated.
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 60
Book Description
For the case of very supersonic leading edges, the inviscid hypersonic flow over the windward side of a symmetrical flat-plate delta wing at incidence is analyzed. The limit selected is that the incidence is of higher order than the aspect ratio as the incidence tends to zero at infinite Mach number. In this framework, the flow regions consist of a two-dimensional domain adjacent to the leading edges and a central conefield. The flow quantities in the central region represent small linear, rotational perturbations about the zero sweep flow. A Riemann-Poincare boundary value problem for the pressure perturbation is formulated. An additional condition involving the sidewash at the shock is found to be required to resolve the indeterminacy of the foregoing boundary value problem. Series solutions and numerical results are presented for the shock shape and the pressure. The behavior of the latter quantity is found to be similar to that given by the irrotational linear solution for the supersonic leading edge case. Finally, the relationship between the present application and others involving diffraction problems and corner flows is indicated.
Applied Mechanics Reviews
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 804
Book Description
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 804
Book Description
Comprehensive Dissertation Index
Author:
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 764
Book Description
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 764
Book Description