Investigation of a Slat in Several Different Positions on an NACA 64A010 Airfoil for a Wide Range of Subsonic Mach Numbers PDF Download
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Author: John A. Axelson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 696
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Book Description
An investigation of the two-dimensional aerodynamic characteristics of an NACA 64A010 airfoil with a slat has been conducted in the Mach number range from 0.25 to 0.85, with a corresponding Reynolds number range from 3.4 million to 8.1 million. Two families of slat positions were investigated, one with the slat leading edge extended forward along the airfoil chord line, and the other with the slat extended forward and displaced below the chord line.
Author: John A. Axelson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 696
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Book Description
An investigation of the two-dimensional aerodynamic characteristics of an NACA 64A010 airfoil with a slat has been conducted in the Mach number range from 0.25 to 0.85, with a corresponding Reynolds number range from 3.4 million to 8.1 million. Two families of slat positions were investigated, one with the slat leading edge extended forward along the airfoil chord line, and the other with the slat extended forward and displaced below the chord line.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 994
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Book Description
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 512
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Book Description
Author: Russell M. Cummings
Publisher: Cambridge University Press
ISBN: 1107053749
Category : Mathematics
Languages : en
Pages : 893
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Book Description
This book covers the application of computational fluid dynamics from low-speed to high-speed flows, especially for use in aerospace applications.
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 56
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Book Description
Author: John A. Kelly
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 706
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Book Description
A previous report, NACA TN 3007, gave force and moment data for the NACA 64A010 airfoil section equipped alternately with a flap and a slat at the leading edge, and with a split flap and a double-slotted flap at the trailing edge. The present report presents the chordwise distributions of pressure measured concurrently with the force and moment data of NACA 3007. The pressure data for the leading-edge flap and slat have been converted into coefficients of normal force, chord force, and moment based on the geometry of the leading-edge device.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 568
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 258
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 750
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 730
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Book Description
