Author: Ernest J Cross (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 136
Book Description
An experimental and analytical investigation was carried out to determine the character of the lee side flow field over a slender delta wing with sharp leading edges in a hypersonic free stream. The experiments of the initial phase of a two part experimental program were for the purpose of obtaining qualitative data to identify the dominant features of the flow field. Schlieren, vapor screen and surface oil flow were useful experimental techniques in this application. The surface pressure, surface temperature, and impact pressure were measured at the points of an extensive array in the lee side flow to determine the magnitude and extent of the flow phenomena. Analysis of the experimental results led to a description of the principal features of the flow field. The character of the flow was identified in three regimes by a specific and dominant property of the flow. The principal concern of this research program was for regime number 2 which had the following characteristics. The viscous flow field on the lee side of the wing caused a significant interaction with the inviscid flow which caused an effective change in the wing geometry. The flow expanded to the displacement boundary layer across the wing leading edge, causing a deflection of the velocity vector toward the plane of symmetry (a plane through the central chord and normal to the surface of the wing), which caused the occurrence of a realignment shock imbedded in the inviscid flow. This shock was sufficiently strong to cause the viscous layer to separate. Results of an impact pressure survey indicated that to a good approximation, the flow field was conical. (Author).
Experimental and Analytical Investigation of the Expansion Flow Field Over a Delta Wing at Hypersonic Speeds
Author: Ernest J Cross (Jr)
Publisher:
ISBN:
Category :
Languages : en
Pages : 136
Book Description
An experimental and analytical investigation was carried out to determine the character of the lee side flow field over a slender delta wing with sharp leading edges in a hypersonic free stream. The experiments of the initial phase of a two part experimental program were for the purpose of obtaining qualitative data to identify the dominant features of the flow field. Schlieren, vapor screen and surface oil flow were useful experimental techniques in this application. The surface pressure, surface temperature, and impact pressure were measured at the points of an extensive array in the lee side flow to determine the magnitude and extent of the flow phenomena. Analysis of the experimental results led to a description of the principal features of the flow field. The character of the flow was identified in three regimes by a specific and dominant property of the flow. The principal concern of this research program was for regime number 2 which had the following characteristics. The viscous flow field on the lee side of the wing caused a significant interaction with the inviscid flow which caused an effective change in the wing geometry. The flow expanded to the displacement boundary layer across the wing leading edge, causing a deflection of the velocity vector toward the plane of symmetry (a plane through the central chord and normal to the surface of the wing), which caused the occurrence of a realignment shock imbedded in the inviscid flow. This shock was sufficiently strong to cause the viscous layer to separate. Results of an impact pressure survey indicated that to a good approximation, the flow field was conical. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 136
Book Description
An experimental and analytical investigation was carried out to determine the character of the lee side flow field over a slender delta wing with sharp leading edges in a hypersonic free stream. The experiments of the initial phase of a two part experimental program were for the purpose of obtaining qualitative data to identify the dominant features of the flow field. Schlieren, vapor screen and surface oil flow were useful experimental techniques in this application. The surface pressure, surface temperature, and impact pressure were measured at the points of an extensive array in the lee side flow to determine the magnitude and extent of the flow phenomena. Analysis of the experimental results led to a description of the principal features of the flow field. The character of the flow was identified in three regimes by a specific and dominant property of the flow. The principal concern of this research program was for regime number 2 which had the following characteristics. The viscous flow field on the lee side of the wing caused a significant interaction with the inviscid flow which caused an effective change in the wing geometry. The flow expanded to the displacement boundary layer across the wing leading edge, causing a deflection of the velocity vector toward the plane of symmetry (a plane through the central chord and normal to the surface of the wing), which caused the occurrence of a realignment shock imbedded in the inviscid flow. This shock was sufficiently strong to cause the viscous layer to separate. Results of an impact pressure survey indicated that to a good approximation, the flow field was conical. (Author).
Experimental and analytical investigation of the expansion flow field over a delta wing at hypersonic speeds
Author: Ernest James Cross
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 240
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 240
Book Description
Experimental and Analytical Investigation of the Expansion Flow Field Over a Delta Wing at Hypersonic Speeds
Author: Ernest James Cross (Jr.)
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
OAR Cumulative Index of Research Results
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1264
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1264
Book Description
An Experimental Investigation of the Expansion Flow Field Over a Delta Wing at Supersonic Speed
Author: W. J. Bannink
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
Book Description
An Experimental Study of the Pressure and Heat-transfer Distribution on a 70° Sweep Slab Delta Wing in Hypersonic Flow
Author: Mitchel H. Bertram
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 134
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 134
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
Monthly Catalog of United States Government Publications
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1932
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1932
Book Description
OAR Progress
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 858
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 858
Book Description