Author: Bruce E. Tinling
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 68
Book Description
A comparison of the lift, drag, and pitching-moment characteristics of several wings having 35 degrees of sweepback and various amounts and various amounts of camber has been made from the results of wind-tunnel tests. Six semispan model wings were tested: three having an aspect ratio of 10, and three having an aspect ratio of 5. The streamwise sections for the three wings of each aspect ratio were the NACA 65(1)A012, the NACA 64(1)A312, and the NACA 64(1)A612. The Reynolds number was varied from 2,000,000 to 10,000,000 at a Mach number of 0.25, and the Mach number was varied from 0.25 to 0.92 at a Reynolds number of 2,000,000.
The Effects of Mach Number and Reynolds Number on the Aerodynamic Characteristics of Several 12-percent-thick Wings Having 35 Degrees of Sweepback and Various Amounts of Camber
Author: Bruce E. Tinling
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 68
Book Description
A comparison of the lift, drag, and pitching-moment characteristics of several wings having 35 degrees of sweepback and various amounts and various amounts of camber has been made from the results of wind-tunnel tests. Six semispan model wings were tested: three having an aspect ratio of 10, and three having an aspect ratio of 5. The streamwise sections for the three wings of each aspect ratio were the NACA 65(1)A012, the NACA 64(1)A312, and the NACA 64(1)A612. The Reynolds number was varied from 2,000,000 to 10,000,000 at a Mach number of 0.25, and the Mach number was varied from 0.25 to 0.92 at a Reynolds number of 2,000,000.
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 68
Book Description
A comparison of the lift, drag, and pitching-moment characteristics of several wings having 35 degrees of sweepback and various amounts and various amounts of camber has been made from the results of wind-tunnel tests. Six semispan model wings were tested: three having an aspect ratio of 10, and three having an aspect ratio of 5. The streamwise sections for the three wings of each aspect ratio were the NACA 65(1)A012, the NACA 64(1)A312, and the NACA 64(1)A612. The Reynolds number was varied from 2,000,000 to 10,000,000 at a Mach number of 0.25, and the Mach number was varied from 0.25 to 0.92 at a Reynolds number of 2,000,000.
Development of an Empirically Based Computer Program to Predict the Aerodynamic Characteristics of Aircraft
Author: Roy T. Schemensky
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 228
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 228
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
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).
A Comparison at Mach Numbers Up to 0.92 of the Calculated and Experimental Downwash and Wake Characteristics at Various Horizonatl Tail Heights Behind a Wing with 45 Degrees of Sweepback
Author: Jack D. Stephenson
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 86
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 86
Book Description
Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 3.96 and 4.63
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
Reynolds Number Effects on the Aerodynamic Characteristics of Irregular Planform Wings at Mach Number 0.3
A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2.0
Author: Robert S. Osborne
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 20
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 20
Book Description
Effects of Increasing Reynolds Number from 2 X 10(exp 6) to 6 X 10(exp 6) on the Aerodynamic Characteristics at Transonic Speeds of a 45 Degree Swept Wing with 6 Degree Leading-edge Droop
Author: James J. Schmeer
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 22
Book Description
An investigation has been made in the Langley 16-foot and 8-foot transonic tunnels to determine the effects of Reynolds number on a swept wing with camber. The wing had 45 degrees sweepback of the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Camber was obtained by drooping the leading edge of the wing 6 degrees about the 19-percent-chord line. Two geometrically similar wing-fuselage configurations were used, one three times as large as the other.
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 22
Book Description
An investigation has been made in the Langley 16-foot and 8-foot transonic tunnels to determine the effects of Reynolds number on a swept wing with camber. The wing had 45 degrees sweepback of the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Camber was obtained by drooping the leading edge of the wing 6 degrees about the 19-percent-chord line. Two geometrically similar wing-fuselage configurations were used, one three times as large as the other.