Author: W.J. Bannink
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Investigation on the Flow Field on the Expansion Side of a Delta Wing with Supersonic Leading Edges
Author: W.J. Bannink
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
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).
An Experimental Investigation of the Flow Fields about Delta and Double-delta Wings at Low Speeds
Author: William H. Wentz (Jr.)
Publisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 160
Book Description
Publisher:
ISBN:
Category : Delta wing airplanes
Languages : en
Pages : 160
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 : 704
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
Book Description
Investigation of Leading-edge Flap Performance on Delta and Double-delta Wings at Supersonic Speeds
Author: Peter F. Covell
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 132
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 132
Book Description
Influence of Airfoil Geometry on Delta Wing Leading-edge Vortices and Vortex-induced Aerodynamics at Supersonic Speeds
Author: Richard M. Wood
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 88
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 88
Book Description
NASA Technical Paper
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 604
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 604
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
Investigation of Leading-edge Flap Performance on Delta and Double-delta Wings at Supersonic Speeds
Author: Peter F. Covell
Publisher:
ISBN:
Category :
Languages : en
Pages : 132
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 132
Book Description