Wind-tunnel Investigation at High Subsonic Speeds to Determine the Rolling Derivatives of Two Wing-fuselage Combinations Having Triangular Winds, Including a Semiempirical Method of Estimating the Rolling Derivatives PDF Download

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Wind-tunnel Investigation at High Subsonic Speeds to Determine the Rolling Derivatives of Two Wing-fuselage Combinations Having Triangular Winds, Including a Semiempirical Method of Estimating the Rolling Derivatives

Wind-tunnel Investigation at High Subsonic Speeds to Determine the Rolling Derivatives of Two Wing-fuselage Combinations Having Triangular Winds, Including a Semiempirical Method of Estimating the Rolling Derivatives PDF Author: James W. Wiggins
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36

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Book Description

Wind-tunnel Investigation at High Subsonic Speeds to Determine the Rolling Derivatives of Two Wing-fuselage Combinations Having Triangular Winds, Including a Semiempirical Method of Estimating the Rolling Derivatives

Wind-tunnel Investigation at High Subsonic Speeds to Determine the Rolling Derivatives of Two Wing-fuselage Combinations Having Triangular Winds, Including a Semiempirical Method of Estimating the Rolling Derivatives PDF Author: James W. Wiggins
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36

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Book Description

Wind-tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13 Degrees and at High Subsonic Mach Numbers, Including a Semiempirical Method of Estimating the Rolling Derivatives

Wind-tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13 Degrees and at High Subsonic Mach Numbers, Including a Semiempirical Method of Estimating the Rolling Derivatives PDF Author: James W. Wiggins
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 47

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Book Description
An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.

Wind-tunnel measurements at subsonic speeds of the static and dynamic-rotary stability derivatives of a triangular-wing airplane model having a triangular vertical tail

Wind-tunnel measurements at subsonic speeds of the static and dynamic-rotary stability derivatives of a triangular-wing airplane model having a triangular vertical tail PDF Author: B.H. Beam
Publisher: Рипол Классик
ISBN: 5873144745
Category : History
Languages : en
Pages : 103

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Book Description
Wind-tunnel measurements at subsonic speeds of the static and dynamic-rotary stability derivatives of a triangular-wing airplane model having a triangular vertical tail.

Wind-tunnel Measurements and Estimated Values of the Rolling Stability Derivatives of a Variable-sweep Airplane Configuration at Subsonic and Transonic Speeds

Wind-tunnel Measurements and Estimated Values of the Rolling Stability Derivatives of a Variable-sweep Airplane Configuration at Subsonic and Transonic Speeds PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 32

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Book Description

A Wind-tunnel Test Technique for Measuring the Dynamic Rotary Stability Derivatives Including the Cross Derivatives at High Mach Numbers

A Wind-tunnel Test Technique for Measuring the Dynamic Rotary Stability Derivatives Including the Cross Derivatives at High Mach Numbers PDF Author: Benjamin H. Beam
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44

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Book Description
A method is described for measuring the dynamic stability derivatives of a model airplane in a wind tunnel. The characteristics features of this system are that single-degree-of-freedom oscillations were used to obtain combinations of rolling, yawing, and pitching motions; that the oscillations were excited and controlled by velocity feedback which permitted operation under conditions unfavorable for more conventional types of oscillatory testing; and that data processing was greatly simplified by using analog computer elements in the strain-gage circuitry.

Wind-tunnel Investigation at High Subsonic Speeds of the Static Longitudinal and Static Lateral Stability Characteristics of a Wing-fuselage Combination Having a Triangular Wing of Aspect Ratio 2.31 and an NACA 65A003 Airfoil

Wind-tunnel Investigation at High Subsonic Speeds of the Static Longitudinal and Static Lateral Stability Characteristics of a Wing-fuselage Combination Having a Triangular Wing of Aspect Ratio 2.31 and an NACA 65A003 Airfoil PDF Author: James W. Wiggins
Publisher:
ISBN:
Category :
Languages : en
Pages : 28

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Book Description

A Wind-tunnel Investigation at Subsonic and Low Supersonic Speeds of a Re-entry Vehicle with Retractable Wings

A Wind-tunnel Investigation at Subsonic and Low Supersonic Speeds of a Re-entry Vehicle with Retractable Wings PDF Author: Willard G. Smith
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 24

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Book Description

Wind-tunnel Investigation of the Aerodynamic Characteristics in Pitch of Wing-fuselage Combinations at High Subsonic Speeds

Wind-tunnel Investigation of the Aerodynamic Characteristics in Pitch of Wing-fuselage Combinations at High Subsonic Speeds PDF Author: James W. Wiggins
Publisher:
ISBN:
Category :
Languages : en
Pages : 41

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Book Description

Wind-tunnel Studies at Subsonic and Transonic Speeds of a Multiple-mission Variable-wing- Sweep Airplane Configuration

Wind-tunnel Studies at Subsonic and Transonic Speeds of a Multiple-mission Variable-wing- Sweep Airplane Configuration PDF Author: William J. Alford
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 82

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Book Description

Wind-tunnel Investigation at Subsonic and Supersonic Speeds of Static and Dynamic Stability Derivatives of Airplane Model with Unswept Wing and High Horizontal Tail [with List of References]

Wind-tunnel Investigation at Subsonic and Supersonic Speeds of Static and Dynamic Stability Derivatives of Airplane Model with Unswept Wing and High Horizontal Tail [with List of References] PDF Author:
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 77

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Book Description