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] PDF Download

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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]

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] PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 39

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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]

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] PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 39

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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

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 PDF Author: John W. Boyd
Publisher:
ISBN:
Category :
Languages : en
Pages : 36

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Book Description

Longitudinal and Lateral Stability and Control Characteristics at Mach Number 2.01 of a 60 Degree Delta-wing Airplane Configuration Equipped with a Canard Control and with Wing Trailing-edge Flap Controls

Longitudinal and Lateral Stability and Control Characteristics at Mach Number 2.01 of a 60 Degree Delta-wing Airplane Configuration Equipped with a Canard Control and with Wing Trailing-edge Flap Controls PDF Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 51

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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

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 PDF Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 36

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Book Description

Static Stability and Control Characteristics of a Triangular Wing and Canard Configuration at Mach Numbers from 2.58 to 3.53

Static Stability and Control Characteristics of a Triangular Wing and Canard Configuration at Mach Numbers from 2.58 to 3.53 PDF Author: C. Ernest Hedstrom
Publisher:
ISBN:
Category :
Languages : en
Pages : 62

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Book Description

Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Trangular Wing and Canard with Twin Vertical Tails

Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Trangular Wing and Canard with Twin Vertical Tails PDF Author: Victor L. Peterson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44

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Book Description

Static Longitudinal Aerodynamic Characteristics of Close-coupled Wing-canard Configurations at Mach Numbers from 1.60 to 2.86

Static Longitudinal Aerodynamic Characteristics of Close-coupled Wing-canard Configurations at Mach Numbers from 1.60 to 2.86 PDF Author: Samuel M. Dollyhigh
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 126

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Book Description
An experimental investigation was made in the Mach number range from 1.60 to 2.86 to determine the static longitudinal aerodynamic characteristics of close-coupled wing-canard configurations. Three canards, ranging in exposed planform area from 17.5 to 30.0 percent of the wing reference area, were employed in this investigation. The canards were either located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. Most data obtained were for a model with a 60 deg leading-edge-sweep wing; however, a small amount of data were obtained for a 44 deg leading-edge-sweep wing. The model utilized two balances to isolate interference effects between wing and canard. In general, it was determined that at angle of attack for all configurations investigated with the canard in the plane of the wing an unfavorable interference exists which causes the additional lift on the canard generated by a canard deflection to be lost on the wing due to an increased downwash at the wing from the canard. Further, this interference decreased somewhat with increasing Mach number. Raising the canard above the plane of the wing also greatly decreased the interference of the canard deflection on the wing lift. However, at Mach 2.86 the presence of the canard in the high position had a greater unfavorable interference effect at high angles of attack than the canard in the wing plane. This interference resulted in the in-plane canard having better trimmed performance at Mach 2.86 for the same center-of-gravity location.

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

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 PDF Author: Jim A. Penland
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 150

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Book Description

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°

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° PDF Author: Gerald V. Foster
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 38

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Book Description

Effects of Wing Height on the Stability and Control Characteristics at a Mach Number of 2.01 of a Canard Airplane Configuration with a 70 Deg Delta Wing

Effects of Wing Height on the Stability and Control Characteristics at a Mach Number of 2.01 of a Canard Airplane Configuration with a 70 Deg Delta Wing PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 36

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Book Description