Investigation of a Twisted Cambered Wing with a 75 Degree Swept Leading Edge at Mach 3 and Reynolds Numbers to 39 X (10)6 PDF Download
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Author: John A. Moore
Publisher:
ISBN:
Category :
Languages : en
Pages : 23
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Book Description
Author: John A. Moore
Publisher:
ISBN:
Category :
Languages : en
Pages : 23
Get Book Here
Book Description
Author: John A. Moore
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 23
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Book Description
![Investigation of a Twisted Cambered Wing with a 75° Swept Leading Edge at Mach 3 and Reynolds Numbers to 39 X 10[hoch6] PDF](https://books.google.com/books/content/images/frontcover/gtq8PgAACAAJ?fife=w80-h100)
Author: John A. Moore
Publisher:
ISBN:
Category :
Languages : en
Pages : 23
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Book Description
Author: John A. Moore
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 34
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1128
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Book Description
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1440
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Book Description
Author: United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1680
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Book Description
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 448
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1426
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Author: Jack F. Runckel
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 104
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Book Description
An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.
