An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degrees Sweepback - Static Lateral Stability Characteristics at Mach Numbers of 1.40 and 1.59 PDF Download
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Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
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Book Description
Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
Get Book Here
Book Description
Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Book Description
Author: John P. Gapcynski
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 28
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Book Description
Author: Ross B. Robinson
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
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Book Description
Author: Charles T. D'Aiutolo
Publisher:
ISBN:
Category : Stability of airplanes, Longitudinal
Languages : en
Pages : 36
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Book Description
Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 22
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Book Description
Author: Clyde V. Hamilton
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
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Book Description
An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61 to determine the stability of control characteristics of a supersonic aircraft configuration with a 40 percent sweptback wing and equipped with spoiler lateral control devices. Some effects of various types of spoilers, spoiler span, projection, and chordwise location were investigated, as well as the hinge-moment characteristics for a plain spoiler.
Author: Norman F. Smith
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 55
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Book Description
A force investigation of a supersonic aircraft configuration and various combinations of its components has been conducted in the Langley 4- by 4-foot supersonic tunnel. The tests were performed at Mach numbers of 1.40 and 1.59 at a Reynolds number of approximately 600,000 based on the wing mean aerodynamic chord and are a part of an extensive investigation of the force and pressure-distribution characteristics of this configuration.
Author: M. Leroy Spearman
Publisher:
ISBN:
Category :
Languages : en
Pages : 27
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Book Description
Author: M. Leroy Spearman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 22
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Book Description
An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a supersonic aircraft configuration equipped with a canard control surface (in addition to a rearward horizontal stabilizer) at a Mach number of 1.89. The model had a 40 degree sweptback tapered wing with an aspect ratio of 4 and 10-percent-thick circular-arc sections normal to the quarter-chord line. The canard surface had a total area about 0ne-twelfth of the total wing area and was located 2.27 mean aerodynamic chord lengths ahead of the reference center of gravity.
