Author: Kenneth P. Spreeman
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description
Small-scale Transonic Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 60 Degrees 42 Minutes Sweptback Wing of Aspect Ratio 1.94
Author: Kenneth P. Spreeman
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description
Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 Degree 38'sweptback Wing of Aspect Ratio 2.98
Author: Kenneth P. Spreeman
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
Book Description
Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 [degrees] 38' Sweptback Wing of Aspect Ratio 2.98
Author: Kenneth P. Spreemann
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
Book Description
Effects of Twist and Camber on the Low-speed Longitudinal Stability Characteristics of a 45© Swept-back Wing of Aspect Ratio 8 at Reynolds Numbers from 1.5 X 106 to 4.8 X 10 as Determined by Pressure Distributions, Force Tests, and Calculations
Author: George L. Pratt
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 110
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 110
Book Description
A Transonic Wind-tunnel Investigation of the Effects of Twist and Camber with and Without Incidence, Twist, and Body Indentation on the Aerodynamic Characteristics of a 45 Degree Sweptback Wing-body Configuration
Author: J. Lawrence Cooper
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Effects of Twist and Camber on the Low-speed Characteristics of a Large-scale 45 Degree Swept-back Wing
Author: Lynn W. Hunton
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Effect of Linear Spanwise Variations of Twist and Circular-Arc Camber on Low-Speed Static Stability, Rolling, and Yawing Characteristics of a 45 Degrees Sweptback Wing of Aspect Ratio 4 and Taper Ration 0.6
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
Book Description
An investigation at low scale has been made in the Langley stab unity tunnel in order to determine the effect of linear spanwise variations of twist and circular-arc camber on the low-speed aerodynamic characteristics and static-stability and rotary-stability (rolling and yawing) derivatives of a wing of aspect ratio 4, taper ratio 0.6, and with 45 deg sweepback of the quarter-chord line. Results of the investigation indicate that twist or camber produced only small changes in the maximum lift coefficient. A combination of camber and twist was more effective than twist alone in providing an increase in the maximum lift-to-drag ratio in the moderate lift-coefficient range for the wings investigated. The variation of static longitudinal stability through the lift-coefficient range was less for the twisted wing than for the twisted and cambered or plane wing. A combination of twist and camber generally extended the initial linear range of several of the static- and rotary-stability derivatives to a higher lift coefficient and, although these effects were small, higher Reynolds numbers may result in larger effects.
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
Book Description
An investigation at low scale has been made in the Langley stab unity tunnel in order to determine the effect of linear spanwise variations of twist and circular-arc camber on the low-speed aerodynamic characteristics and static-stability and rotary-stability (rolling and yawing) derivatives of a wing of aspect ratio 4, taper ratio 0.6, and with 45 deg sweepback of the quarter-chord line. Results of the investigation indicate that twist or camber produced only small changes in the maximum lift coefficient. A combination of camber and twist was more effective than twist alone in providing an increase in the maximum lift-to-drag ratio in the moderate lift-coefficient range for the wings investigated. The variation of static longitudinal stability through the lift-coefficient range was less for the twisted wing than for the twisted and cambered or plane wing. A combination of twist and camber generally extended the initial linear range of several of the static- and rotary-stability derivatives to a higher lift coefficient and, although these effects were small, higher Reynolds numbers may result in larger effects.
Cost Utilization Analysis of Inhaled Steroids for Allergic Rhinitis Management
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3, a Taper Ratio of 0.2, and Naca 65a004 Airfoil Sections
Author: JACK F. RUNCKEL
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections was conducted in the Langley 16-foot transonic tunnel. Pressure measurements on the wing-body combi ation were obtained at angles of attack from 0 degrees to 26 degrees at Mach numbers from 0.80 to 0.98 and at angles of attack from 0 degrees to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic c ord varied from 7 times 10 to the 6th po er to 8.5 times 10 to the 6th power over the test Mach number range. Results of the investigation indicate that a highly swept shock originates at the juncture of the wing leading edge and the body at moderate angles of attack and has a large influence on the loading over the inboard wing sections. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections was conducted in the Langley 16-foot transonic tunnel. Pressure measurements on the wing-body combi ation were obtained at angles of attack from 0 degrees to 26 degrees at Mach numbers from 0.80 to 0.98 and at angles of attack from 0 degrees to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic c ord varied from 7 times 10 to the 6th po er to 8.5 times 10 to the 6th power over the test Mach number range. Results of the investigation indicate that a highly swept shock originates at the juncture of the wing leading edge and the body at moderate angles of attack and has a large influence on the loading over the inboard wing sections. (Author).
A Study of the Effect of Leading-edge Modifications on the Flow Over a 50 Degrees Sweptback Wing at Transonic Speeds
Author: E. W. E. Rogers
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description