Book description
This high-level aerospace reference book will be useful for undergraduate and graduate students of engineering, applied mathematics and physics. The author provides solutions for three-dimensional compressible Navier-Stokes layer subsonic and supersonic flows.* Computational work and experimental results show the real-world application of computational results
* Easy computation and visualization of inviscid and viscous aerodynamic characteristics of flying configurations
* Includes a fully optimized and integrated design for a proposed supersonic transport aircraft
Table of contents
- Cover image
- Title page
- Table of Contents
- Dedication
- Copyright
- About the Author
- Preface
- Acknowledgments
-
Chapter 1: Zonal, Spectral Solutions for the Three-Dimensional, Compressible Navier–Stokes Layer
- 1.1. Introduction
- 1.2. Three-dimensional, partial-differential equations of compressible Navier-Stokes layer (NSL)
- 1.3. The spectral variable and the spectral forms of the velocity’s components and of the physical entities
- 1.4. The first and second derivatives of the velocity’s components
- 1.5. The implicit and explicit forms of the boundary conditions at the NSL’s edge
- 1.6. The dependence of the density function R versus the spectral velocity, inside the NSL
- 1.7. Dependence of absolute temperature T versus the spectral velocity, inside the NSL
- 1.8. The scalar forms of the NSL’s impulse’s partial-differential equations and their equivalent quadratical algebraic equations
- 1.9. Determination of spectral coefficients of the velocity’s components by solving an equivalent quadratical algebraic system, via the collocation method
- 1.10. An original iterative method to solve a quadratical algebraic system
- 1.11. Conclusions
-
Chapter 2: Hyperbolical Potential Boundary Value Problems of the Axial Disturbance Velocities of Outer Flow, at NSL’s Edge
- 2.1. Introduction
- 2.2. Basic equations
- 2.3. Full-linearized partial-differential equations of the flow over flattened, flying configurations
- 2.4. The characteristic hypersurfaces of the partial-differential equations of second order
- 2.5. The linearized pressure coefficient Cp on flying configurations
- 2.6. The linearized boundary value problems for flying configurations, at moderate angles of attack α
- 2.7. Definitions and properties of the thin and thick-symmetrical components of the thick, lifting flying configurations
- 2.8. The disturbance regions produced by a moving point in subsonic and supersonic flow
- 2.9. Disturbance regions and characteristic surfaces produced by triangular wings, in supersonic flow
- 2.10. Disturbance regions and characteristic surfaces produced by trapezoidal wings, in supersonic flow
- 2.11. Disturbance regions and characteristic surfaces produced by rectangular wings, in supersonic flow
- 2.12. The boundary value problems for the axial disturbance velocities on thin and thick-symmetrical wedged triangular wing components, in supersonic flow
- 2.13. Conclusions
-
Chapter 3: Computation of Axial Disturbance Velocities on Wedged Wings, in Supersonic Flow, at NSL’s Edge
- 3.1. General considerations
- 3.2. The conical flow of first order
- 3.3. The boundary conditions for the wedged triangular wings, in the Germain’s plane
- 3.4. The solutions of direct boundary value problems for U and U* on wedged triangular wing components
- 3.5. The complex axial disturbance velocities U and U* on the wedged triangular wing components
- 3.6. The axial disturbance velocities u and u* on the wedged delta wing components
- 3.7. The axial disturbance velocities u and u* on the wedged trapezoidal wing components
- 3.8. The axial disturbance velocities u and u* on the wedged rectangular wing components
- 3.9. Conclusions
-
Chapter 4: Computation of Axial Disturbance Velocities on Flying Configurations with Arbitrary Shapes, in Supersonic Flow, at NSL’s Edge
- 4.1. General considerations
- 4.2. The theory of high conical flow of nth order
- 4.3. The principle of minimal singularities for the high conical flow of nth order
- 4.4. The solutions of boundary value problems of fictitious complex potentials Ff and Ff*, on triangular wings
- 4.5. The axial disturbance velocities on the thin and thick-symmetrical triangular wings with arbitrary shapes
- 4.6. The axial disturbance velocities on delta wings with arbitrary shapes
- 4.7. The axial disturbance velocities on trapezoidal wings with arbitrary shapes
- 4.8. The axial disturbance velocities on rectangular wings with arbitrary shapes
- 4.9. The axial disturbance velocities on non-integrated or integrated delta wing-fuselage configurations
- 4.10. The axial disturbance velocities on non-integrated or integrated delta wing-fuselage configurations with movable leading edge flaps
- 4.11. Determination of the constants of axial disturbance velocities on flying configurations
- 4.12. Conclusions
-
Chapter 5: The Aerodynamical Characteristics of Flying Configurations with Arbitrary Shapes, in Supersonic Flow
- 5.1. General considerations
- 5.2. The computation of the aerodynamical characteristics of the delta wings
- 5.3. The computation of the aerodynamical characteristics of delta wing-fuselage configurations
- 5.4. The computation of the aerodynamical characteristics of delta wing-fuselage configurations, fitted with leading edge flaps, in open positions
- 5.5. The computation of the lift, pitching moment and drag coefficients of the rectangular wings
- 5.6. Conclusions
-
Chapter 6: The Visualizations of the Surfaces of Pressure Coefficients and Aerodynamical Characteristics of Wedged Delta and Wedged Rectangular Wings, in Supersonic Flow
- 6.1. Introduction
- 6.2. The three-dimensional visualizations of the Cp-surfaces on the LAF’s wedged delta wing, in supersonic flow
- 6.3. Visualizations of the behaviors of the Cp-surfaces on a wedged delta wing, by crossing of sonic lines
- 6.4. Visualizations of the surfaces of lift and pitching moment coefficients of LAF’s wedged delta wing and of their asymptotical behaviors, by crossing of sonic lines
- 6.5. The visualization of the inviscid drag coefficient’s surface of the LAF’s wedged delta wing and of its asymptotical behavior, by crossing of sonic lines
- 6.6. The polar surface of the LAF’s wedged delta wing and its asymptotical behavior, by crossing of sonic lines
- 6.7. The visualizations of the Cp-surfaces on the LAF’s wedged rectangular wing
- 6.8. The behaviors of the Cp-surfaces by changing of the LAF’s wedged rectangular wing from long to short, at ν = 1
- 6.9. The three-dimensional visualizations of surfaces of aerodynamical characteristics of LAF’s wedged rectangular wing
- 6.10. The polar surface of the LAF’s wedged rectangular wing, in supersonic flow
- 6.11. Conclusions
-
Chapter 7: Qualitative Analysis of the NSL’s Asymptotical Behaviors in the Vicinity of its Critical Zones
- 7.1. Introduction
- 7.2. Reduction of quadratical, elliptical and hyperbolical algebraic equations to their canonical forms
- 7.3. The asymptotical behaviors of quadratical algebraic equations with variable free term
- 7.4. The qualitative analysis of elliptical and hyperbolical, quadratical, algebraic equations with variable coefficients of free and linear terms
- 7.5. The Jacobi determinant and the Jacobi hypersurface
- 7.6. The aerodynamical applications of the qualitative analysis of the QAEs
- 7.7. Conclusions
- Chapter 8: Computation of the Friction Drag Coefficients of the Flying Configurations
-
Chapter 9: Inviscid and Viscous Aerodynamical Global Optimal Design
- 9.1. Introduction
- 9.2. The optimum–optimorum theory
- 9.3. Inviscid aerodynamical global optimal design, via optimum–optimorum theory
- 9.4. Inviscid aerodynamic global optimal design of delta wing model ADELA, via optimum–optimorum theory
- 9.5. Inviscid aerodynamic global optimal design of fully-integrated wing/fuselage models FADET I and FADET II
- 9.6. The iterative optimum–optimorum theory and the viscous aerodynamical optimal design
- 9.7. Proposal for a fully-optimized and fully-integrated Catamaran STA
- 9.8. Conclusions
-
Chapter 10: Comparison of the Theoretical Aerodynamical Characteristics of Wing Models with Experimental-Determined Results
- 10.1. Introduction
- 10.2. The aims of the experimental program
- 10.3. Determination of experimental-correlated values of aerodynamical characteristics and of interpolated values of pressure coefficient
- 10.4. Comparison of theoretical aerodynamical characteristics of LAF’s wedged delta wing model with experimental results
- 10.5. Comparison of theoretical aerodynamical characteristics of LAF’s double wedged delta wing model with experimental results
- 10.6. Comparison of theoretical aerodynamical characteristics of LAF’s wedged delta wing model, fitted with a conical fuselage, with experimental results
- 10.7. Comparison of theoretical aerodynamical characteristics of LAF’s fully-optimized delta wing model ADELA with experimental results
- 10.8. Comparison of theoretical aerodynamical characteristics of LAF’s wedged rectangular wing model with experimental results
- 10.9. Comparison of theoretical aerodynamic characteristics of LAF’s cambered rectangular wing model with experimental results
- 10.10. Conclusions
- Final Remarks
- Outlook
- Author Index
- Subject Index
Product information
- Title: Computation of Supersonic Flow over Flying Configurations
- Author(s):
- Release date: July 2010
- Publisher(s): Elsevier Science
- ISBN: 9780080556994
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