Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 46
Book Description
Effects of Wing Sweep and Horizontal-tail Position on the Aerodynamic Characteristics at a Mach Number of 2.2 of a Variable-sweep Airplane Configuration Having an Inboard Wing Pivot
The Effects of Horizontal-tail Position on the Longitudinal Aerodynamic Characteristics at Transonic Speeds of a Variable-sweep Aircraft Having an Inboard Pivot
Low-speed Aerodynamic Characteristics of a Double-pivot Variable-wing-sweep Airplane Configuration Having Conventional and Outboard Horizontal Tail Surfaces
Effect of Wing Pivot Location on Longitudinal Aerodynamic Characteristics of a Variable-sweep Wing Having an M Planform
Author: William P. Henderson
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 48
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 48
Book Description
Stability and Control Characteristics at a Mach Number of 1.41 of a Variable-sweep Airplane Configuration Capable of Low-level Supersonic Attack-outer Wing Swept 75°and 108°
Author: Ross B. Robinson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 32
Book Description
Investigation of the Aerodynamic Characteristics in Pitch and Sideslip of a 45© Swept-wing Airplane Configuration with Various Vertical Locations of the Wing and Horizontal Tail
Author: M. Leroy Spearman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 34
Book Description
An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 34
Book Description
An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.