Elsevier S & T

Computation of Supersonic Flow over Flying Configurations

Nastase, Adriana

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Table of contents

Contentsv
About the Authorxiii
Prefacexv
Acknowledgmentsxvii
Chapter 1 Zonal, Spectral Solutions for the Three-Dimensional, Compressible Navier–Stokes Layer1
1.1 Introduction1
1.2 Three-dimensional, partial-differential equations of compressible Navier–Stokes layer (NSL)2
1.3 The spectral variable and the spectral forms of the velocity's components and of the physical en4
1.4 The first and second derivatives of the velocity's components5
1.5 The implicit and explicit forms of the boundary conditions at the NSL's edge8
1.6 The dependence of the density function R versus the spectral velocity, inside the NSL10
1.7 Dependence of absolute temperature T versus the spectral velocity, inside the NSL11
1.8 The scalar forms of the NSL's impulse's partial-differential equations and their equivalent quad12
1.9 Determination of spectral coefficients of the velocity's components by solving an equivalent qua15
1.10 An original iterative method to solve a quadratical algebraic system16
1.11 Conclusions18
References19
Chapter 2 Hyperbolical Potential Boundary Value Problems of the Axial Disturbance Velocities of Oute20
2.1 Introduction20
2.2 Basic equations21
2.3 Full-linearized partial-differential equations of the flow over flattened, flying configurations26
2.4 The characteristic hypersurfaces of the partial-differential equations of second order28
2.4.1 The classification of quasi-linear partial-differential equations of second order28
2.4.2 The characteristic's condition and the characteristic hypersurface30
2.5 The linearized pressure coefficient C[sub(p)] on flying configurations33
2.6 The linearized boundary value problems for flying configurations, at moderate angles of attack &34
2.7 Definitions and properties of the thin and thick-symmetrical components of the thick, lifting fl35
2.8 The disturbance regions produced by a moving point in subsonic and supersonic flow38
2.9 Disturbance regions and characteristic surfaces produced by triangular wings, in supersonic flow40
2.10 Disturbance regions and characteristic surfaces produced by trapezoidal wings, in supersonic fl49
2.11 Disturbance regions and characteristic surfaces produced by rectangular wings, in supersonic fl52
2.12 The boundary value problems for the axial disturbance velocities on thin and thick-symmetrical53
2.13 Conclusions56
References57
Chapter 3 Computation of Axial Disturbance Velocities on Wedged Wings, in Supersonic Flow, at NSL's58
3.1 General considerations58
3.2 The conical flow of first order60
3.2.1 Definition of the conical flow60
3.2.2 The Germain's complex plane61
3.2.3 The Germain's compatibility conditions for the conical flow63
3.2.4 The Carafoli's hydrodynamic analogy for the conical flow63
3.2.5 The principle of the minimal singularities for the wedged triangular wings65
3.3 The boundary conditions for the wedged triangular wings, in the Germain's plane68
3.3.1 Introduction68
3.3.2 The boundary conditions of the fictitious, complex potentials U and U* on the real axis of the68
3.3.3 The wedged triangular wings with one subsonic and one supersonic leading edge72
3.3.4 The wedged triangular wings with two supersonic leading edges73
3.4 The solutions of direct boundary value problems for U and U* on wedged triangular wing component78
3.4.1 The auxiliary plane χ=λ+iμ78
3.4.2 The affine transformed wing and the transformed complex plane x78
3.4.3 The contribution of a subsonic leading edge on the thin wedged triangular wing80
3.4.4 The contributions of ridges of the thin and thick-symmetrical wedged triangular wings82
3.4.5 The contribution of the supersonic leading edge on the thin wedged triangular wing84
3.4.6 The contributions of the leading edges on the thick-symmetrical wedged triangular wings85
3.5 The complex axial disturbance velocities U and U* on the wedged triangular wing components85
3.5.1 Introduction85
3.5.2 The complex axial disturbance velocity U on the thin wedged triangular wing86
3.5.3 The complex axial disturbance velocity U* on the thick-symmetrical wedged triangular wing88
3.6 The axial disturbance velocities u and u* on the wedged delta wing components91
3.7 The axial disturbance velocities u and u* on the wedged trapezoidal wing components95
3.8 The axial disturbance velocities u and u* on the wedged rectangular wing components101
3.9 Conclusions102
References103
Chapter 4 Computation of Axial Disturbance Velocities on Flying Configurations with Arbitrary Shapes106
4.1 General considerations106
4.2 The theory of high conical flow of nth order107
4.2.1 Definition of the high conical flow of the nth order and the homogeneity conditions107
4.2.2 The Germain's compatibility conditions for the high conical flow of nth order111
4.2.3 The Carafoli's hydrodynamic analogy for the high conical flow of nth order112
4.2.4 The boundary conditions of the fictitious, complex potentials F[sub(f)] and Fast*[sub(f)], on114
4.3 The principle of minimal singularities for the high conical flow of nth order119
4.4 The solutions of boundary value problems of fictitious complex potentials F[sub(f)] and F*[sub(f121
4.5 The axial disturbance velocities on the thin and thick-symmetrical triangular wings with arbitra129
4.6 The axial disturbance velocities on delta wings with arbitrary shapes135
4.7 The axial disturbance velocities on trapezoidal wings with arbitrary shapes137
4.8 The axial disturbance velocities on rectangular wings with arbitrary shapes140
4.9 The axial disturbance velocities on non-integrated or integrated delta wing-fuselage configurati142
4.10 The axial disturbance velocities on non-integrated or integrated delta wing-fuselage configurat147
4.11 Determination of the constants of axial disturbance velocities on flying configurations151
4.12 Conclusions152
References153
Chapter 5 The Aerodynamical Characteristics of Flying Configurations with Arbitrary Shapes, in Super156
5.1 General considerations156
5.2 The computation of the aerodynamical characteristics of the delta wings158
5.3 The computation of the aerodynamical characteristics of delta wing-fuselage configurations165
5.4 The computation of the aerodynamical characteristics of delta wing-fuselage configurations, fitt172
5.5 The computation of the lift, pitching moment and drag coefficients of the rectangular wings180
5.6 Conclusions185
References185
Chapter 6 The Visualizations of the Surfaces of Pressure Coefficients and Aerodynamical Characterist188
6.1 Introduction188
6.2 The three-dimensional visualizations of the C[sub(p)]-surfaces on the LAF's wedged delta wing, i189
6.3 Visualizations of the behaviors of the C[sub(p)]-surfaces on a wedged delta wing, by crossing of199
6.4 Visualizations of the surfaces of lift and pitching moment coefficients of LAF's wedged delta wi201
6.5 The visualization of the inviscid drag coefficient's surface of the LAF's wedged delta wing and202
6.6 The polar surface of the LAF's wedged delta wing and its asymptotical behavior, by crossing of s204
6.7 The visualizations of the C[sub(p)]-surfaces on the LAF's wedged rectangular wing207
6.8 The behaviors of the C[sub(p)]-surfaces by changing of the LAF's wedged rectangular wing from lo213
6.9 The three-dimensional visualizations of surfaces of aerodynamical characteristics of LAF's wedge215
6.10 The polar surface of the LAF's wedged rectangular wing, in supersonic flow219
6.11 Conclusions220
References222
Chapter 7 Qualitative Analysis of the NSL's Asymptotical Behaviors in the Vicinity of its Critical Z224
7.1 Introduction224
7.2 Reduction of quadratical, elliptical and hyperbolical algebraic equations to their canonical for226
7.3 The asymptotical behaviors of quadratical algebraic equations with variable free term228
7.3.1 General considerations228
7.3.2 The qualitative analysis of the behaviors of quadratical, elliptical, algebraic equations in t229
7.3.3 The qualitative analysis of the behaviors of quadratical, hyperbolical, algebraic equations in237
7.4 The qualitative analysis of elliptical and hyperbolical, quadratical, algebraic equations with v247
7.4.1 General considerations247
7.4.2 The collapse of the elliptical QAEs along their critical parabola248
7.4.3 The degeneration of the hyperbolical QAEs along their critical parabola250
7.5 The Jacobi determinant and the Jacobi hypersurface251
7.6 The aerodynamical applications of the qualitative analysis of the QAEs252
7.7 Conclusions253
References254
Chapter 8 Computation of the Friction Drag Coefficients of the Flying Configurations256
8.1 Introduction256
8.2 Computation of the inviscid lateral velocity υ, at the NSL's edge258
8.3 The coupling between the NSL's slopes and the velocity field263
8.4 Computation of friction and total drag coefficients of the delta wings264
8.5 Conclusions266
References267
Chapter 9 Inviscid and Viscous Aerodynamical Global Optimal Design269
9.1 Introduction269
9.2 The optimum–optimorum theory271
9.3 Inviscid aerodynamical global optimal design, via optimum–optimorum theory273
9.4 Inviscid aerodynamic global optimal design of delta wing model ADELA, via optimum–optimorum th277
9.5 Inviscid aerodynamic global optimal design of fully-integrated wing/fuselage models FADET I and279
9.6 The iterative optimum–optimorum theory and the viscous aerodynamical optimal design283
9.7 Proposal for a fully-optimized and fully-integrated Catamaran STA285
9.8 Conclusions287
References288
Chapter 10 Comparison of the Theoretical Aerodynamical Characteristics of Wing Models with Experimen292
10.1 Introduction292
10.2 The aims of the experimental program293
10.3 Determination of experimental-correlated values of aerodynamical characteristics and of interpo297
10.4 Comparison of theoretical aerodynamical characteristics of LAF's wedged delta wing model with e299
10.4.1 The description of LAF's wedged delta wing model299
10.4.2 The computation of axial disturbance velocities on the upper side of wedged delta wings299
10.4.3 The comparison of the theoretical and experimental-correlated values of C[sub(l)] and C[sub(m304
10.5 Comparison of theoretical aerodynamical characteristics of LAF's double wedged delta wing model311
10.5.1 The description of LAF's double wedged delta wing model311
10.5.2 Computation of downwashes and of axial disturbance velocities on double wedged delta wing314
10.5.3 Comparison of theoretical and experimental-correlated C[sub(l)] and C[sub(m)] of LAF's double316
10.6 Comparison of theoretical aerodynamical characteristics of LAF's wedged delta wing model, fitte319
10.6.1 Description of LAF's delta wing-fuselage model319
10.6.2 The computation of downwashes and of axial disturbance velocities on the wedged delta wing mo320
10.6.3 Comparison of the theoretical and experimental-correlated values C[sub(l)] and C[sub(m)] of L324
10.7 Comparison of theoretical aerodynamical characteristics of LAF's fully-optimized delta wing mod327
10.7.1 Description of LAF's fully-optimized delta wing model ADELA327
10.7.2 The computation of downwashes and of axial disturbance velocities on the fully-optimized delt330
10.7.3 Comparison of theoretical and experimental-correlated values of C[sub(l)] and C[sub(m)] of LA332
10.8 Comparison of theoretical aerodynamical characteristics of LAF's wedged rectangular wing model336
10.8.1 Description of LAF's wedged rectangular wing model336
10.8.2 The computation of axial disturbance velocities on wedged rectangular wing model339
10.8.3 The comparison of theoretical and experimental-correlated values of C[sub(l)] and C[sub(m)] o340
10.9 Comparison of theoretical aerodynamic characteristics of LAF's cambered rectangular wing model343
10.9.1 Description of LAF's cambered rectangular wing model343
10.9.2 Computation of the axial disturbance velocities on LAF's cambered rectangular wing model344
10.9.3 The comparison of theoretical and experimental-correlated values of C[sub(l)] and C[sub(m)] o347
10.10 Conclusions349
References352
Final Remarks354
Outlook356
Author Index357
Subject Index361
Plate Section391

Book details

Vendor Elsevier S & T
SKU 9780080449579
ISBN-13 9780080556994
Author Nastase, Adriana
Category Technology & Engineering
Subject Aeronautics & Astronautics

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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

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