Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 968
Book Description
Scientific and Technical Aerospace Reports
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 968
Book Description
An Investigation of the Flow Characteristics in the Blade Endwall Corner Region
Author: Birinchi K. HazarikaPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 296
Book Description
Dissertation Abstracts International
Author: Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 750
Book Description
Mean velocities and Reynolds stresses in a juncture flow
Author: H. McMahonPublisher:
ISBN:
Category : Reynolds stresses
Languages : en
Pages : 128
Book Description
Mean Velocities and Reynolds Stresses Upstream of a Simulated Wing-fuselage Juncture
Author: H. McMahonPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 176
Book Description
An Experimental Study of Near Wall Flow Parameters in the Blade End-wall Corner Region
Author: Rakesh K. BhargavaPublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 320
Book Description
Symposium on Naval Hydrodynamics
Author: Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 634
Book Description
NASA Contractor Report
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 424
Book Description
American Doctoral Dissertations
Author: Publisher:
ISBN:
Category : Dissertation abstracts
Languages : en
Pages : 604
Book Description
Interference Drag in a Simulated Wing-fuselage Juncture
Author: L. R. KubendranPublisher:
ISBN:
Category : Interference (Aerodynamics)
Languages : en
Pages : 66
Book Description
The interference drag in a wing fuselage juncture as simulated by a flat plate and a body of constant thickness having a 1.5:1 elliptical leading edge is evaluated experimentally. The experimental measurements consist of mean velocity data taken with a hot wire at a streamwise location corresponding to 16 body widths downstream of the body leading edge. From these data, the interference drag is determined by calculating the total momentum deficit (momentum area) in the juncture and also in the two dimensional turbulent boundary layers on the flat plate and body at locations sufficiently far from the juncture flow effect. The interference drag caused by the juncture drag as measured at this particular streamwise station is -3% of the total drag due to the flat plate and body boundary layers in isolation. If the body is considered to be a wing having a chord and span equal to 16 body widths, the interference drag due to the juncture is only -1% of the frictional drag of one surface of such a wing.
