Author: Emma Jean Landrum
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 24
Book Description
Effect of Shape Changes on the Aerodynamic Characteristics of a Twisted and Cambered Arrow Wing at Mach Number 2.03
Author: Emma Jean Landrum
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 24
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 24
Book Description
Longitudinal Aerodynamic Characteristics at Mach Number 2.02 of a Series of Wing-body Configurations Employing a Cambered and Twisted Arrow Wing
Effects of Shape Changes on the Aerodynamic Characteristics of a Twisted and Cambared Arrow Wing at Mach Number 2.03
Effects of Twist and Camber and Thickness on the Aerodynamic Characteristics of a 75° Swept Arrow Wing at a Mach Number of 2.91
Author: James N. Mueller
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 72
Book Description
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 72
Book Description
Effects at Mach Numbers of 1.61 and 2.01 of Camber and Twist on the Aerodynamic Characteristics of Three Swept Wings Having the Same Planform
Author: Emma Jean Landrum
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 52
Book Description
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 52
Book Description
Off-design Aerodynamic Characteristics at Mach Numbers 1.61 and 2.20 of a Series of Highly Swept Arrow Wings Designed for Mach Number 2.0 Employing Various Degrees of Twist and Camber
Author: Wilbur D. Middleton
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
Aerodynamic Characteristics at Mach Number 2.05 of a Series of Highly Swept Arrow Wings Employing Various Degrees of Twist and Camber
Author: Harry W. Carlson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 38
Book Description
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 38
Book Description
Aerodynamic Characteristics at Mach Numbers from 1.6 to 2.8 of 740 Swept Arrow Wings with and Without Camber and Twist
Author: Dennis F. Hasson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 42
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 42
Book Description
Aerodynamic Characteristics at Mach Numbers from 2.29 to 4.65 of 80 Deg Swept Arrow Wings with and Without Camber and Twist
Effects at Mach Numbers of 1.61 and 2.01 of Camber and Twist on the Aerodynamic Characteristics of Three Swept Wings Hafing the Same Planform
Author: EMMA JEAN. LANDRUM
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
An investigation has been made at Mach numbers of 1.61 and 2.01 to determine the aerodynamic characteristics of three wings having a sweepback of 50 degrees at the quarter-chord line, a taper ratio of 0.20, an NACA 65A005 thickness distribution, and an aspect ratio of 3.5. One wing was flat, one had at each spanwise station an a equals 0 mean line modified to have a maximum height of 4% chord, and one had a linear variation of twist with 6 degrees of washout at the tip. When compared with the flat wing, the effect of the linear variation of twist with 6 degrees of washout at the tip was to increase the lift-drag ratio when the leading edge was subsonic; but little increase in lift-drag ratio was obtained when the leading edge was supersonic. Pitching moment was increased and gave a positive trim point without greatly affecting the rate of change of pitching moment with lift coefficient. For the cambered wing the high minimum drag resulted in comparatively low liftdrag ratios. In addition, the pitching moments were decreased so that a negative trim point was obtained. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
An investigation has been made at Mach numbers of 1.61 and 2.01 to determine the aerodynamic characteristics of three wings having a sweepback of 50 degrees at the quarter-chord line, a taper ratio of 0.20, an NACA 65A005 thickness distribution, and an aspect ratio of 3.5. One wing was flat, one had at each spanwise station an a equals 0 mean line modified to have a maximum height of 4% chord, and one had a linear variation of twist with 6 degrees of washout at the tip. When compared with the flat wing, the effect of the linear variation of twist with 6 degrees of washout at the tip was to increase the lift-drag ratio when the leading edge was subsonic; but little increase in lift-drag ratio was obtained when the leading edge was supersonic. Pitching moment was increased and gave a positive trim point without greatly affecting the rate of change of pitching moment with lift coefficient. For the cambered wing the high minimum drag resulted in comparatively low liftdrag ratios. In addition, the pitching moments were decreased so that a negative trim point was obtained. (Author).