Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
Book Description
Aerodynamic Characteristics at a Mach Number of 2.20 of a Variable-sweep Fighter Model with Wing Sweep of 50 Deg, 60 Deg, and 75 Deg
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
Book Description
Transonic Longitudinal Aerodynamic Characteristics of a Model of a Tactical Fighter Airplane with a Fixed Delta Wing and Variable-sweep Wing Panels
Author: Richard J. Re
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
Book Description
Transonic Aerodynamic Characteristics of a Variable-sweep Airplane Configuration Having a 12-percent-thick Wing and an Inboard Pivot Location
Author: Ralph P. Bielat
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 84
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 84
Book Description
Transonic Longitudinal Aerodynamic Characteristics of a Variable-sweep Fighter Model Having Body-mounted Nacelles
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 54
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 54
Book Description
Longitudinal and Lateral Aerodynamic Characteristics at Mach Numbers from 0.60 to 2.20 of a Variable Sweep Fighter Model with Wing Sweep Angles from 25 Deg to 75 Deg
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
Book Description
The Longitudinal and Lateral Aerodynamic Characteristics at Mach Numbers of 1.41 and 2.20 of a Variable-sweep Fighter Model with Wing Sweeps Varying from 25 Deg to 75 Deg
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
Book Description
Transonic Aerodynamic Characteristics of a Variable-wing-sweep Tactical Fighter Model
Author: Theodore G. Ayers
Publisher:
ISBN:
Category :
Languages : en
Pages : 35
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 35
Book Description
Transonic Aerodynamic Characteristics of a Variable-wing-sweep Tactical Fighter Model
Author: Theodore G. Ayers
Publisher:
ISBN:
Category :
Languages : en
Pages : 96
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 96
Book Description
Transonic Longitudinal Aerodynamic Characteristics of an STOL Fighter-bomber Model with a Variable-sweep Wing
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 118
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 118
Book Description
Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches
Author: Charles F. Whitcomb
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 34
Book Description
An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 34
Book Description
An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.