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 PDF Download

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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

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 PDF Author: Kenneth P. Spreeman
Publisher:
ISBN:
Category :
Languages : en
Pages : 18

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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

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 PDF Author: Kenneth P. Spreeman
Publisher:
ISBN:
Category :
Languages : en
Pages : 18

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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

Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 Degree 38'sweptback Wing of Aspect Ratio 2.98 PDF Author: Kenneth P. Spreeman
Publisher:
ISBN:
Category :
Languages : en
Pages : 30

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Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 [degrees] 38' Sweptback Wing of Aspect Ratio 2.98

Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 50 [degrees] 38' Sweptback Wing of Aspect Ratio 2.98 PDF Author: Kenneth P. Spreemann
Publisher:
ISBN:
Category :
Languages : en
Pages : 30

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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

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 PDF Author: George L. Pratt
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 110

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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

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 PDF Author: J. Lawrence Cooper
Publisher:
ISBN:
Category :
Languages : en
Pages : 36

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Book Description

Effects of Twist and Camber on the Low-speed Characteristics of a Large-scale 45 Degree Swept-back Wing

Effects of Twist and Camber on the Low-speed Characteristics of a Large-scale 45 Degree Swept-back Wing PDF Author: Lynn W. Hunton
Publisher:
ISBN:
Category :
Languages : en
Pages : 36

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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

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 PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 30

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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

Cost Utilization Analysis of Inhaled Steroids for Allergic Rhinitis Management PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :

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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

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 PDF Author: JACK F. RUNCKEL
Publisher:
ISBN:
Category :
Languages : en
Pages : 1

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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

A Study of the Effect of Leading-edge Modifications on the Flow Over a 50 Degrees Sweptback Wing at Transonic Speeds PDF Author: E. W. E. Rogers
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Book Description