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Theoretical characteristics of two-dimensional supersonic control surfaces
- Author / Creator
- Available as
- Online
- Summary
-
The "Busemann second-order-approximiation theory" for the pressure distribution over a two-dimensional airfoil in supersonic flow was used to determine some of the aerodynamic characteristics of un...
The "Busemann second-order-approximiation theory" for the pressure distribution over a two-dimensional airfoil in supersonic flow was used to determine some of the aerodynamic characteristics of uncambered symmetrical parabolic and double-wedge airfoils with leading-edge and trailing edge flaps. The characteristics presented and discussed in this paper are: flap effectiveneess factor, rate of change of hinge-moment coefficient with flap deflection, rate of change of pitching-moment coefficient about the midchord with flap deflection, and the location of the center of pressure of the airfoil-flap combination.
Details
- Creator
- by Robert R. Morrissette and Lester F. Oborny
- Format
- Books
- Language
- English
- Contributors
- Publication
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- Washington, D.C. : National Advisory Committee for Aeronautics, 1951
- Physical Details
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- 1 online resource (74 pages) : illustrations, tables
- data file
- OCLC
- on1336511440
- "Langley Aeronautical Laboratory."
- Title from title screen (viewed July 14, 2022)
- Date of issue: October 1951.
- Report numbers NACA-TN-2486.
- Includes bibliographical references (page 17)
- Electronic reproduction. Denton, Texas : University of North Texas, 2011. Electronic reproduction from print master produced by University of North Texas.