Laminar Boundary Layer on a Circular Cone in Supersonic Flow at a Small Angle of Attack PDF Download
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Author: Franklin K. Moore
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 710
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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.
Author: Franklin K. Moore
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 710
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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.
Author: Cornell University. Graduate School of Aeronautical Engineering
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Martin Fiebig
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 0
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Author: Willis H. Braun
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1216
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Book Description
Author: Willis H. Braun
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
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Book Description
The momentum integral equations are derived for the boundary layer on an arbitrary curved surface, using a streamline coordinate system. Computations of the turbulent boundary layer on a slightly yawed cone are made for a Prandtl number of 0.729, wall to free-stream temperature ratios of 1/2, 1, and 2, and Mach numbers from 1 to 4. Deflection of the fluid in the boundary layer from outer stream direction, local friction coefficient, displacement surface, lift coefficient, and pitching-moment coefficient are presented.
Author: Arloe Wesley Mayne (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 114
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Author: Franklin K. Moore
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 13
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Book Description
The laminar-boundary-layer flow about a cone at large angles of attack to a supersonic stream has been analyzed in the plane of symmetry. At the bottom of the cone, velocity profiles were obtained showing the expected tendency of the boundary layer to become thinner on the under side of the cone as the angle of attack is increased. At the top of the cone, the analysis failed to yield unique solutions, except for small angles of attack. Beyond a certain critical angle of attack, boundary-layer flow does not exist in the plane of symmetry, thus indicating separation.
Author: Joseph L. Sims
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 440
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 372
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Book Description
