Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Longitudinal Stability and Control Characteristics at Mach Numbers of 1.41 and 2.01 of a 67 Degree Swept-wing Airplane Configuration with Canard Control Surfaces
Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Wing-flow Measurements of Longitudinal Stability and Control Characteristics of a Canard Airplane Configuration with a 45 Degree Sweptback Wing and a Triangular All-movable Control Surface
Author: Harold L. Crane
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 53
Book Description
Measurements of the longitudinal stability and control characteristics of a canard airplane configuration have been made by the wing-flow method. The distinguishing features of this configuration in addition to the unconventional wing-stabilizer arrangement are the triangular plan form of the all-movable longitudinal control surface, the 45 degree sweptback wing of aspect ratio 4.1, and the slender body of fineness ratio 13.5. The investigation included measurements of lift, pitching moment, and rolling moment of the semispan model, with control settings between -4 degrees and 16 degrees and with the control surface removed. In some cases the angle-of-attack range was as great as from approximately -10 to 30 degrees. Approximate measurements of chord force were made at one stabilizer incidence. The Mach number range covered was from 0.55 to 1.14 at Reynolds numbers of the order of 400,000.
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 53
Book Description
Measurements of the longitudinal stability and control characteristics of a canard airplane configuration have been made by the wing-flow method. The distinguishing features of this configuration in addition to the unconventional wing-stabilizer arrangement are the triangular plan form of the all-movable longitudinal control surface, the 45 degree sweptback wing of aspect ratio 4.1, and the slender body of fineness ratio 13.5. The investigation included measurements of lift, pitching moment, and rolling moment of the semispan model, with control settings between -4 degrees and 16 degrees and with the control surface removed. In some cases the angle-of-attack range was as great as from approximately -10 to 30 degrees. Approximate measurements of chord force were made at one stabilizer incidence. The Mach number range covered was from 0.55 to 1.14 at Reynolds numbers of the order of 400,000.
Stability and Control Characteristics at Mach Numbers of 2.50, 3.00, and 3.71 of a Variable- Wing-sweep Configuration with Outboard Wing Panels Swept Back 75°
Author: Gerald V. Foster
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 38
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 38
Book Description
Longitudinal Stability and Control Characteristics at Mach Numbers from 0.70 to 2.22 of a Triangular Wing Configuration Equipped with a Canard Control, a Trailing-edge-flap Control, Or a Cambered Forebody
Author: John W. Boyd
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Stability and Control Characteristics at a Mach Number of 1.97 of an Airplane Configuration Having Two Types of Variable- Sweep Wings
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 48
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 48
Book Description
Wing-flow Measurements of Longitudinal Stability and Control Characteristics of a Canard Airplane Configuration with a 45 Degrees Sweptback Wing and a Triangular Alll-movable Control Surface
Author: Harold L. Crane
Publisher:
ISBN:
Category :
Languages : en
Pages : 53
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 53
Book Description
Longitudinal Stability and Control Characteristics at Mach Numbers from 0.70 to 2.22 of Triangular Wing Configuration Equipped with Canard Control, Trailing-edge Flap Control, Or Cambered Forebody [with List of References]
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 39
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 39
Book Description
Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Longitudinal Characteristics of an Unswept Wing and Canard
Author: Victor L. Peterson
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 29
Book Description
The results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration are presented without analysis for the Mach number range from 0.70 to 2.22. The configuration consisted of an aspect ratio 3.1 unswept wing, an aspect ratio 3.0 unswept canard, a low aspect ratio vertical tail, and a Sears-Haack body. The hinge line of the canard was in the extended chord plane of the wing, 1.33 wing mean aerodynamic chords ahead of the reference center of moments. The ratio of the area of the exposed canard panels to the total area of the wing is 8.1 percent. Data are presented for various combinations of the canard, wing, and vertical tail for an angle-of-attack range from -6 to 18 degrees. The canard deflection angles ranged from 0 to 20 degrees.
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 29
Book Description
The results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration are presented without analysis for the Mach number range from 0.70 to 2.22. The configuration consisted of an aspect ratio 3.1 unswept wing, an aspect ratio 3.0 unswept canard, a low aspect ratio vertical tail, and a Sears-Haack body. The hinge line of the canard was in the extended chord plane of the wing, 1.33 wing mean aerodynamic chords ahead of the reference center of moments. The ratio of the area of the exposed canard panels to the total area of the wing is 8.1 percent. Data are presented for various combinations of the canard, wing, and vertical tail for an angle-of-attack range from -6 to 18 degrees. The canard deflection angles ranged from 0 to 20 degrees.
Stability and Control Characteristics at a Mach Number of 2.01 of a Variable-wing-sweep Configuration with Outboard Wing Panels Swept Back 75 Deg
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Book Description
Static Longitudinal, Directional, and Lateral Stability and Control Data at a Mach Number of 6.83 of the Final Configuration of the X-15 Research Airplane
Author: Jim A. Penland
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 150
Book Description
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 150
Book Description