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Characteristics at Mach Number of 2.03 of a Series of Wings Having Various Spanwise Distributions of Thickness Ration and Chord

Characteristics at Mach Number of 2.03 of a Series of Wings Having Various Spanwise Distributions of Thickness Ration and Chord PDF Author: A. Warner Robins
Publisher:
ISBN:
Category :
Languages : en
Pages : 30

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Book Description

Characteristics at Mach Number of 2.03 of a Series of Wings Having Various Spanwise Distributions of Thickness Ration and Chord

Characteristics at Mach Number of 2.03 of a Series of Wings Having Various Spanwise Distributions of Thickness Ration and Chord PDF Author: A. Warner Robins
Publisher:
ISBN:
Category :
Languages : en
Pages : 30

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Book Description

Characteristics at Mach Number of 2.03 of a Series of Wings Having Various Spanwise Distributions of Thickness Ratio and Chord

Characteristics at Mach Number of 2.03 of a Series of Wings Having Various Spanwise Distributions of Thickness Ratio and Chord PDF Author: A. Warner Robins
Publisher:
ISBN:
Category :
Languages : en
Pages : 26

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Book Description

Characteristics at Mach Number of 2.03 of a Series of Wings Having Various Spanwise Distributions of Thickness Ration and Chord

Characteristics at Mach Number of 2.03 of a Series of Wings Having Various Spanwise Distributions of Thickness Ration and Chord PDF Author: A. Warner Robins
Publisher:
ISBN:
Category :
Languages : en
Pages : 26

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Book Description

Zero-lift Drag at Mach 1.42, 1.83, and 2.21 of a Series of Wings with Variations of Thickness Ratio and Chord

Zero-lift Drag at Mach 1.42, 1.83, and 2.21 of a Series of Wings with Variations of Thickness Ratio and Chord PDF Author: Barrett L. Shrout
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 26

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Book Description

Span Loadings and Aerodynamic Characteristics for a Series of Tip and Trailing-edge Controls on a 60° Delta Wing at Mach Numbers of 1.61 and 2.01

Span Loadings and Aerodynamic Characteristics for a Series of Tip and Trailing-edge Controls on a 60° Delta Wing at Mach Numbers of 1.61 and 2.01 PDF Author: K. R. Czarnecki
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 124

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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

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 PDF Author: Emma Jean Landrum
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 52

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Book Description

Calculation of Aerodynamic Loading and Twist Characteristics of a Flexible Wing at Mach Numbers Approaching 1.0 and Comparison with Experiment

Calculation of Aerodynamic Loading and Twist Characteristics of a Flexible Wing at Mach Numbers Approaching 1.0 and Comparison with Experiment PDF Author: John P.. Mugler
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 40

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Book Description

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

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 PDF Author: Jack D. Stephenson
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 86

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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

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 PDF Author: EMMA JEAN. LANDRUM
Publisher:
ISBN:
Category :
Languages : en
Pages : 1

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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).

Applied Mechanics Reviews

Applied Mechanics Reviews PDF Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 1006

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Book Description