[PDF] Full Investigation Of A Slat In Several Different Positions On An Naca 64a010 Airfoil For A Wide Range Of Subsonic Mach Numbers Download eBook

Investigation of a Slat in Several Different Positions on an NACA 64A010 Airfoil for a Wide Range of Subsonic Mach Numbers

Author: John A. Axelson

Publisher:

Published: 1954

Total Pages: 696

ISBN-13:

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.

Technical Note - National Advisory Committee for Aeronautics

Author: United States. National Advisory Committee for Aeronautics

Publisher:

Published: 1954

Total Pages: 994

ISBN-13:

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U.S. Government Research Reports

Author:

Publisher:

Published: 1954

Total Pages: 512

ISBN-13:

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Applied Computational Aerodynamics

Author: Russell M. Cummings

Publisher: Cambridge University Press

Published: 2015-04-27

Total Pages: 893

ISBN-13: 1107053749

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This book covers the application of computational fluid dynamics from low-speed to high-speed flows, especially for use in aerospace applications.

Bibliography of Technical Reports

Author:

Publisher:

Published: 1954

Total Pages: 56

ISBN-13:

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Aerodynamic Loads on a Leading-edge Flap and a Leading-edge Slat on the NACA 64A010 Airfoil Section

Author: John A. Kelly

Publisher:

Published: 1954

Total Pages: 706

ISBN-13:

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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.