Author: Warren A. Tucker
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 19
Book Description
Equations were found for the lift coefficient, rolling-moment coefficient, and hinge-moment coefficient due to control deflection, and for the pitching-moment coefficient due to flap lift. The effect of thickness was shown to be given by a single factor.
Theoretical Characteristics in Supersonic Flow of Constant-chord Partial-span Control Surfaces on Rectangular Wings Having Finite Thickness
Author: Warren A. Tucker
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 19
Book Description
Equations were found for the lift coefficient, rolling-moment coefficient, and hinge-moment coefficient due to control deflection, and for the pitching-moment coefficient due to flap lift. The effect of thickness was shown to be given by a single factor.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 19
Book Description
Equations were found for the lift coefficient, rolling-moment coefficient, and hinge-moment coefficient due to control deflection, and for the pitching-moment coefficient due to flap lift. The effect of thickness was shown to be given by a single factor.
Theoretical Characteristics in Supersonic Flow of Constant-Chord Partial-Span Control Surfaces on Rectangular Wings
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Some Theoretical Characteristics of Trapezoidal Wings in Supersonic Flow and a Comparison of Several Wing-flap Combinations
Author: Robert O. Piland
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
The theoretical lift and pitching moment due to angle of attack and pitching and the lateral force and yawing moment due to rolling of a trapezoidal wing are derived. The equations are applicable when the inboard Mach line from a leading-edge tip intersects the trailing edge and the outboard Mach line lies ahead of the side edge. When the side edges are raked in, the former condition is sufficient. A comparison based on theoretical expressions of the lift and rolling effectiveness for half-delta tip (point forward) and trailing-edge flaps on various plan forms is made.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
The theoretical lift and pitching moment due to angle of attack and pitching and the lateral force and yawing moment due to rolling of a trapezoidal wing are derived. The equations are applicable when the inboard Mach line from a leading-edge tip intersects the trailing edge and the outboard Mach line lies ahead of the side edge. When the side edges are raked in, the former condition is sufficient. A comparison based on theoretical expressions of the lift and rolling effectiveness for half-delta tip (point forward) and trailing-edge flaps on various plan forms is made.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1056
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1056
Book Description
Report - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
Book Description
Annual Report of the National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 692
Book Description
Includes the Committee's Reports no. 1-1058, reprinted in v. 1-37.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 692
Book Description
Includes the Committee's Reports no. 1-1058, reprinted in v. 1-37.
Correlation of Cylinder-head Temperatures and Coolant Heat Rejections of a Multicylinder, Liquid-cooled Engine of 1710-cubic-inch Displacement
Author: Bruce T. Lundin
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 262
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 262
Book Description
NASA Technical Note
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 424
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 424
Book Description
The Application of Green's Theorem to the Solution of Boundary-value Problems in Linearized Supersonic Wing Theory
Author: Max A. Heaslet
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 656
Book Description
Under the assumptions of linearized theory, general methods of solutin are given for two- and three-dimensional steady-state and two-dimensional unsteady-state equations of compressible flow. The solutions depend in all cases on the use of Green's equivalent layer of sources, sinks, and doublets. Emphasis is placed on applications in supersonic wing theory, the singularities arising in the integrations being treated by Hadamard's finite part of the technique. Four examples of different character are discussed. In particular, the load distribution over a specific swept-back lifting surface is determined at a free-stream Mach number of one.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 656
Book Description
Under the assumptions of linearized theory, general methods of solutin are given for two- and three-dimensional steady-state and two-dimensional unsteady-state equations of compressible flow. The solutions depend in all cases on the use of Green's equivalent layer of sources, sinks, and doublets. Emphasis is placed on applications in supersonic wing theory, the singularities arising in the integrations being treated by Hadamard's finite part of the technique. Four examples of different character are discussed. In particular, the load distribution over a specific swept-back lifting surface is determined at a free-stream Mach number of one.
The Rolling Moment Due to Sideslip of Triangular, Trapezoidal, and Related Plan Forms in Supersonic Flow
Author: Arthur L. Jones
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 644
Book Description
The variation of the rolling moment with sideslip and the variation of the derivative with aspect ratio and Mach number were investigated.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 644
Book Description
The variation of the rolling moment with sideslip and the variation of the derivative with aspect ratio and Mach number were investigated.