http://www.loc.gov/mods/v3 http://www.loc.gov/standards/mods/v3/mods-3-2.xsd
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.
Front Cover; Wing Theory in Supersonic Flow; Copyright Page; Table of Contents; PREFACE; ACKNOWLEDGEMENTS; CHAPTER I. RECAPITULATIVE SURVEY OF THE EQUATIONS OF MOTIONOF PERFECT FLUIDS IN SUPERSONIC FLOW; I. 1. General Equations; I. 2. Propagation of Small Disturbances; I. 3. Velocity Potential Equation; I. 4. Pressure Coefficient under the Assumption of Small Disturbances; I. 5. Theory of Wings of Infinite Aspect Ratio in Supersonic Flow underthe Assumption of Small Disturbances.
I. 6. Theory of Axially-symmetric Bodies under the Assumption of SmallDisturbances (Application to the Circular Cone)I. 7. Conical Motions in Supersonic Flow; I. 8. High-order Conical Flows; CHAPTER II. UNIFIED THEORY OF ANGULAR WINGS BASED ON HIGH-ORDERCONICAL FLOW DETERMINATION OF THE AXIAL DISTURBANCE VELOCITY(u) AND OF THE DOWNWASH (w) IN THE DIRECT, INDIRECT ANDMIXED PROBLEMS; II. 1. General Considerations; CHAPTERIII. THE CALCULATION OF THE OVERALL FORCES AND MOMENTS ONWINGS WITH TRAILING EDGES OF ARBITRARY PLANFORM SHAPE.
II. 2. Behaviour of the Axial Disturbance Velocity u in the Neighbourhoodof the Subsonic Leading Edges or the Subsonic Ridges on the ThinWing (Direct Problem)II. 3. Contribution of the Subsonic Leading Edges of Thin Wings and of the Separation Ridges to the Construction of the Velocity u (DirectProblem); II. 4. Examples of Application to Ordinary Wings in the Direct Problem; II. 5. Determination of Constants; II. 6. Examples of the Determination of Constants.
II. 7. Contribution of the Ridges and the Leading Edge to the Calculation ofthe Downwash w, when the Pressures are given on the Wing(Indirect Problem)II. 8. Some Considerations on the Indirect Problem; II. 9. Wing whose Incidence Variation and Pressure Distribution are givenAlternatively on Separate Portions (Mixed Problem); III. 1. Preliminary Considerations; III. 2. Calculation of Forces; III. 3. Calculation of Moments; III. 4. Some Special Applications of the Formulae for Calculating the Forcesand Moments.
III. 5. Calculation of the Suction Force induced by the Subsonic LeadingEdges of a Thin WingCHAPTERIV. STUDY OF ORDINARY DELTA WINGS; IV. 1. Introductory Considerations on the Delta Wing; IV. 2. Thin Delta Wing with Subsonic Leading Edges having SymmetricalIncidences; IV. 3. Thin Delta Wing with Subsonic Edges having Antisymmetrical Incidences; IV. 4. Thin Delta Wing with Supersonic Edges and Symmetry of Incidence; IV. 5. Wing of Symmetrical Thickness; IV. 6. Thin Delta Wing with Supersonic Edges and Antisymmetry of Incidence; IV. 7. Delta Wing with Sonic Leading Edges.
by Elie Carafoli ; with the cooperation of Dan Mateescu and Adriana Nastase.
Master and use copy. Digital master created according to Benchmark for Faithful Digital Reproductions of Monographs and Serials, Version 1. Digital Library Federation, December 2002. http://purl.oclc.org/DLF/benchrepro0212 MiAaHDL
digitized 2010 HathiTrust Digital Library committed to preserve pda MiAaHDL
Includes bibliographical references (pages 565-588).
International series of monographs in aeronautics and astronautics. v. 7