Theoretical Study Of Air Forces On An Oscillating Or Steady Thin Wing In A Supersonic Main Stream
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| Author | : Isadore Edward Garrick |
| Publisher | : |
| Total Pages | : 50 |
| Release | : 1947 |
| Genre | : Aerodynamic load |
| ISBN | : |
This paper constitutes a theoretical study of the aerodynamic forces on an oscillating or steady wing of finite span moving forward at a uniform supersonic speed. The treatment is based on the linearized theory obtained by considering only small disturbances in an ideal fluid. The wing is therefore considered to be a nearly flat thin surface at a small angle of attack and the flow is considered non- viscous and free of strong shocks. The theory in this case is equivalent to finding certain solutions of the wave equation in three dimensions with respect to a moving coordinate system.
| Author | : Douglas Godfrey |
| Publisher | : |
| Total Pages | : 690 |
| Release | : 1950 |
| Genre | : Fretting corrosion |
| ISBN | : |
Fretting corrosion was concluded to be caused by the removal of finely divided and apparently virgin material due to inherent forces and that its primary reaction is independent of of vibratory motion or high sliding speeds. Fretting corrosion occurred to clean nonmetals and metals readily and glass microscope slides and steel balls provided an excellent method for visual studies.
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 1076 |
| Release | : 1958 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : Albert E. Von Doenhoff |
| Publisher | : |
| Total Pages | : 668 |
| Release | : 1953 |
| Genre | : Dichlorodifluoromethane |
| ISBN | : |
A number of studies relating to the use of Freon-12 as a substitute medium for air in aerodynamic testing have been made. The use of Freon-12 instead of air makes possible large savings in wind-tunnel drive power. Because of the fact that the ratio of specific heats is approximately 1.13 for Freon-12 as compared with 1.4 for air, some differences exist between data obtained in Freon-12 and air. Methods for predicting aerodynamic characteristics of bodies in air from data obtained in Freon-12, however, have been developed from the concept of similarity of the streamline pattern. These methods, derived from consideration of two-dimensional flows, provide substantial agreement in all cases for which comparative data are available. These data consist of measurements throughout a range of Mach number from approximately 0.4 to 1.2 of pressure distributions and hinge moments on swept and unswept wings having aspect ratios ranging from 4.0 to 9.0, including cases where a substantial part of the wing was stalled.
| Author | : |
| Publisher | : |
| Total Pages | : 354 |
| Release | : 1975 |
| Genre | : Airplanes |
| ISBN | : |
| Author | : James T. Matthews |
| Publisher | : |
| Total Pages | : 726 |
| Release | : 1958 |
| Genre | : Acceleration (Mechanics) |
| ISBN | : |
A theoretical analysis was made to investigate the performance and acceleration-restriction capabilities of a normal-acceleration command control system in a fighter airplane. Several combinations of pitching velocity and pitching acceleration were investigated as feedback quantities in combination with normal acceleration.
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 446 |
| Release | : 1947 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : Robert T. Jones |
| Publisher | : |
| Total Pages | : 708 |
| Release | : 1950 |
| Genre | : Airplanes |
| ISBN | : |
The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. Expressions for the spanwise load distribution and the minimum drag in terms of the lateral position of the load centroid are given. The results show a 15-percent reduction of the induced drag with a 15-percent increase in span over that for an elliptic loading having the same total lift and bending moment.
| Author | : Elie Carafoli |
| Publisher | : Elsevier |
| Total Pages | : 611 |
| Release | : 2013-10-22 |
| Genre | : Technology & Engineering |
| ISBN | : 1483160270 |
Division II: Aerodynamics, Volume 7: Wing Theory in Supersonic Flow examines the cases of isolated simple wings, wings with vertical plane tail, cruciform wings, and simple or cruciform wings fitted with a body. This book presents the method for the actual calculation of isolated wings or of more complex system. Organized into 12 chapters, this volume starts with an overview of the basic equations in the mechanics of inviscid fluids. This text then presents a unified theory that is established for angularly shaped wings in supersonic flow. Other chapters consider the method for calculating the characteristics of drag, lift, and moments for various shapes of the trailing edge line. This book discusses as well the wings of ordinary shapes, delta wings, yawed wings, polygonal wings, trapezoid wings, and arrow-head or swept-back wings. The final chapter deals with a delta wing with a central fusiform body. This book is a valuable resource for teachers, students, and specialists engaged in modern aerodynamics.
| Author | : Manuel Stein |
| Publisher | : |
| Total Pages | : 694 |
| Release | : 1950 |
| Genre | : Aeronautics |
| ISBN | : |
A small-deflection theory that takes into account deformations due to transverse shear is presented for the elastic-behavior analysis of orthotropic plates of constant cylindrical curvature, with considerations of buckling included. The theory is applicable primarily to sandwich construction.
