This document discusses the aerodynamic characteristics of lifting surfaces like wings. It examines how factors like aspect ratio, sweep angle, and taper ratio impact the lift coefficient and its derivative with respect to angle of attack. Higher aspect ratio, lower sweep angle, and lower taper ratio generally result in a higher lift coefficient derivative. The lift coefficient relationship becomes non-linear for wings with very small aspect ratios, less than 1. Formulas are provided to calculate the lift coefficient, its derivative, and the angle of zero lift based on the wing geometry.
The Mean Value Theorem is the Most Important Theorem in Calculus. It allows us to relate information about the derivative of a function to information about the function itself.
The Mean Value Theorem is the most important theorem in calculus! It allows us to infer information about a function from information about its derivative. Such as: a function whose derivative is zero must be a constant function.
The document discusses the aerodynamic characteristics of bodies of revolution like fuselages. It provides formulas to calculate:
1) The lift coefficient of different parts (nose, cylindrical, rear) of a body of revolution, accounting for factors like cross-sectional area changes, Mach number, boundary layers, etc.
2) The derivative of the lift coefficient of different parts, which depends on parameters like nose shape, aspect ratios, Mach number.
3) The aerodynamic moment of different parts and the coordinate of the aerodynamic center, calculated using formulas based on the elongated body theory.
This document provides an overview of key concepts in calculus related to derivatives, including: analyzing functions to determine if they are increasing or decreasing; finding relative extrema, critical points, and inflection points; using the first and second derivative tests to determine concavity; and graphing polynomials. Examples are provided to illustrate how to apply these concepts to specific functions in order to analyze intervals of increase/decrease, locate critical points, identify relative maxima and minima, and determine intervals of concavity. Videos and Khan Academy links are also included for supplemental instruction on related topics.
The document discusses polar equations and their use in representing conic sections. It defines key terms like focus, directrix, and eccentricity used to describe ellipses, parabolas, and hyperbolas. Ellipses and hyperbolas are defined geometrically as all points where the distance to one focus (PF) divided by the distance to the corresponding directrix (PD) is a constant (the eccentricity). Examples are given of the polar forms of different conic sections for varying eccentricities.
The document provides a math review covering topics in algebra, geometry, trigonometry, and statistics. It defines concepts like negative numbers, exponents, square roots, order of operations, lines, angles, trigonometric functions, and averages. Formulas are presented for topics like quadratic equations, the Pythagorean theorem, laws of sines and cosines, percentages, and standard deviation. Examples are included to illustrate key ideas.
This document defines and discusses parabolas. It begins by listing 4 learning outcomes related to understanding parabolas, their standard form equations, graphing them, and solving problems involving parabolas. It then defines a parabola as the set of all points that are the same distance from both a fixed focus point and directrix line. The standard form of the equation for a parabola is derived and explained to be x^2 = 4cy, where c is the distance between the focus and directrix. Key features of parabolas like the vertex, directrix, focus, and axis of symmetry are identified. Examples of determining standard equations and graphing parabolas are provided.
The document discusses calculating the area swept out by a polar function r=f(θ) between the angles θ=a and θ=b. The polar area formula is given as A = (1/2) ∫f(θ)2 dθ. Formulas are derived to integrate the squares of sine and cosine in terms of the cosine double angle. These integrals are summarized. An example problem finds the area swept by r=2sin(θ) between 0 and 2π, which is 2π, the area of a circle with radius 1 swept out twice.
The Mean Value Theorem is the Most Important Theorem in Calculus. It allows us to relate information about the derivative of a function to information about the function itself.
The Mean Value Theorem is the most important theorem in calculus! It allows us to infer information about a function from information about its derivative. Such as: a function whose derivative is zero must be a constant function.
The document discusses the aerodynamic characteristics of bodies of revolution like fuselages. It provides formulas to calculate:
1) The lift coefficient of different parts (nose, cylindrical, rear) of a body of revolution, accounting for factors like cross-sectional area changes, Mach number, boundary layers, etc.
2) The derivative of the lift coefficient of different parts, which depends on parameters like nose shape, aspect ratios, Mach number.
3) The aerodynamic moment of different parts and the coordinate of the aerodynamic center, calculated using formulas based on the elongated body theory.
This document provides an overview of key concepts in calculus related to derivatives, including: analyzing functions to determine if they are increasing or decreasing; finding relative extrema, critical points, and inflection points; using the first and second derivative tests to determine concavity; and graphing polynomials. Examples are provided to illustrate how to apply these concepts to specific functions in order to analyze intervals of increase/decrease, locate critical points, identify relative maxima and minima, and determine intervals of concavity. Videos and Khan Academy links are also included for supplemental instruction on related topics.
The document discusses polar equations and their use in representing conic sections. It defines key terms like focus, directrix, and eccentricity used to describe ellipses, parabolas, and hyperbolas. Ellipses and hyperbolas are defined geometrically as all points where the distance to one focus (PF) divided by the distance to the corresponding directrix (PD) is a constant (the eccentricity). Examples are given of the polar forms of different conic sections for varying eccentricities.
The document provides a math review covering topics in algebra, geometry, trigonometry, and statistics. It defines concepts like negative numbers, exponents, square roots, order of operations, lines, angles, trigonometric functions, and averages. Formulas are presented for topics like quadratic equations, the Pythagorean theorem, laws of sines and cosines, percentages, and standard deviation. Examples are included to illustrate key ideas.
This document defines and discusses parabolas. It begins by listing 4 learning outcomes related to understanding parabolas, their standard form equations, graphing them, and solving problems involving parabolas. It then defines a parabola as the set of all points that are the same distance from both a fixed focus point and directrix line. The standard form of the equation for a parabola is derived and explained to be x^2 = 4cy, where c is the distance between the focus and directrix. Key features of parabolas like the vertex, directrix, focus, and axis of symmetry are identified. Examples of determining standard equations and graphing parabolas are provided.
The document discusses calculating the area swept out by a polar function r=f(θ) between the angles θ=a and θ=b. The polar area formula is given as A = (1/2) ∫f(θ)2 dθ. Formulas are derived to integrate the squares of sine and cosine in terms of the cosine double angle. These integrals are summarized. An example problem finds the area swept by r=2sin(θ) between 0 and 2π, which is 2π, the area of a circle with radius 1 swept out twice.
The Mean Value Theorem is the most important theorem in calculus. It is the first theorem which allows us to infer information about a function from information about its derivative. From the MVT we can derive tests for the monotonicity (increase or decrease) and concavity of a function.
This document is the cover page for a mathematics preliminary examination. It provides instructions for candidates taking the exam, including writing their identification information, answering all questions, showing necessary work, using calculators appropriately, and specifying the degree of accuracy for answers. It also lists several mathematical formulas that may be useful for the exam, such as formulas for compound interest, mensuration, trigonometry, and statistics. The total number of marks for the exam is 80.
(1) The document is an examination paper for Secondary 4/5 students in mathematics. It consists of 13 printed pages containing 11 questions testing various math concepts.
(2) Instructions are provided for candidates, including writing their name, working clearly, using calculators where appropriate, and expressing some answers to a given degree of accuracy or in terms of pi.
(3) The exam covers topics like algebra, trigonometry, geometry, calculus, statistics, and financial mathematics. Questions involve factorizing expressions, solving equations, using circle properties, graphing functions, and probability.
The document discusses properties and equations of circles, including the standard form of a circle equation with a given center and radius. It also discusses tangent lines to circles, providing the process and equations for finding the equation of a tangent line to a circle at a given
The document describes Lagrange multipliers, which are used to find the extrema (maximum and minimum points) of a function subject to a constraint. Specifically:
1) A function z=f(x,y) defines a surface, and an equation g(x,y)=0 defines a curve on the xy-plane.
2) The points where this curve intersects the surface form a "trail".
3) The extrema on this trail occur where the gradients of the surface and constraint are parallel (or equivalently where their normals are parallel), allowing the use of Lagrange multipliers to solve the constrained optimization problem.
The document discusses tangent planes to surfaces. A surface is differentiable at a point if it is smooth and has a well-defined tangent plane at that point. The tangent plane approximates the surface near the point of tangency. To find the equation of the tangent plane, we calculate the partial derivatives of the surface function at the point to determine the slopes in the x- and y-directions. These slopes and the point define vectors in the tangent plane, and their cross product gives the normal vector. The equation of the tangent plane is then (z - c) = M(x - a) + L(y - b), where M and L are the partial derivatives and (a, b, c) is the
The document discusses parabolas and their key properties. It defines a parabola as the set of all points equidistant from a fixed point (the focus) and a line (the directrix). The line perpendicular to the directrix through the focus is called the axis. The point where the parabola intersects the axis is the vertex. Parabolas have reflecting properties such that light rays entering parallel to the axis will exit through the focus. This allows parabolic dishes to focus collected radio waves or light at a single point. The document also provides examples of graphing parabolas and finding their equations based on given properties, as well as calculating dimensions of the Hubble Space Telescope's parabolic mirror.
1. The document discusses techniques for finding extrema of functions, including absolute and local extrema. Critical points, endpoints, and the first and second derivative tests are covered.
2. The mean value theorem and Rolle's theorem are summarized. The mean value theorem relates the average and instantaneous rates of change over an interval.
3. Optimization problems can be solved by setting the derivative of the objective function equal to zero to find critical points corresponding to maxima or minima.
4. Newton's method is presented as an iterative process for approximating solutions to equations, using tangent lines to generate a sequence of improving approximations.
5. Anti-derivatives are defined as functions whose derivatives are a given
The document discusses graphs in polar coordinates. It begins by reviewing how polar coordinates (r, θ) represent a point P, where r is the distance from the origin and θ is the angle relative to the x-axis. It then discusses how to convert between rectangular (x, y) and polar (r, θ) coordinates. The document explains that polar equations relate r and θ, giving the example of r = θ which graphs as an Archimedean spiral. It also discusses the graphs of constant equations like r = c, which is a circle, and θ = c, which is a line. The document concludes by explaining how to graph other polar equations by plotting points.
This document is a chapter from an introductory mathematical analysis textbook. It covers curve sketching, including how to find relative and absolute extrema, determine concavity, use the second derivative test, identify asymptotes, and apply concepts of maxima and minima. The chapter contains learning objectives, an outline of topics, examples of applying techniques to sketch curves and solve optimization problems, and instructional content to introduce these curve sketching concepts.
The document describes how the Smith Chart maps impedances on the normalized complex impedance plane to the complex Γ plane. Vertical lines on the impedance plane representing constant resistance values r map to circles on the Γ plane, with centers located along the Γi = 0 line. Horizontal lines representing constant reactance values x also map to circles, with centers located along the Γr = 1 line. By mapping many such lines, the rectilinear grid of the impedance plane is distorted into the curvilinear grid of circles that make up the Smith Chart.
The document discusses the Smith chart, a graphical method for analyzing transmission lines. It provides advantages of using the Smith chart such as facilitating complex number calculations and visualizing transmission line systems. The basics of the Smith chart are outlined, including key reference points and how to plot complex impedances, move along the chart, and solve problems involving impedance matching. Several examples are worked through demonstrating using the Smith chart to find input impedance, reflection coefficient, and VSWR for different transmission line scenarios.
The Smith Chart provides a graphical tool for analyzing transmission lines and impedance matching circuits. It maps the reflection coefficient Γ onto a two-dimensional plane defined by the magnitude and phase of Γ. Transformations of Γ along a transmission line correspond to moving along a circular arc on the Smith Chart, allowing problems involving transmission line impedance transformations to be solved graphically. Special cases like quarter-wave and half-wave transmission lines correspond to rotations of 90 and 180 degrees on the Smith Chart.
This document introduces graph C*-algebras and related concepts:
- A graph C*-algebra is generated by partial isometries and projections representing a directed graph.
- A Cuntz-Krieger E-family satisfies relations involving these operators to represent a graph as bounded operators on a Hilbert space.
- The graph C*-algebra is then the closed algebra generated by this family of operators.
Intuitionistic First-Order Logic: Categorical semantics via the Curry-Howard ...Marco Benini
A novel approach to giving an interpretation of logic inside category theory. This work has been developed as part of my sabbatical Marie Curie fellowship in Leeds.
Presented at the Logic Seminar, School of Mathematics, University of Leeds (2012).
This document contains the questions and solutions from the First Semester B.E. Degree Examination in Engineering Mathematics from January 2013. It includes 10 multiple choice questions testing concepts in calculus, differential equations, and linear algebra. It also contains 4 full problems to solve related to derivatives, integrals, differential equations, and vectors/matrices.
The document discusses multi-variable functions and how to visualize them. It defines Rn as the set of n-tuples of real numbers. A n-variable real valued function maps from Rn to the real numbers. Level curves are used to visualize functions of two variables by setting z equal to constants and plotting the resulting equations in the x-y plane. This produces families of curves that depict the shape of the surface. Examples show how different functions produce different level curve shapes like ellipses, hyperbolas or parabolas.
The leadership of the Utilitas Mathematica Journal commits to strengthening our professional community by making it more just, equitable, diverse, and inclusive. We affirm that our mission, Promote the Practice and Profession of Statistics, can be realized only by fully embracing justice, equity, diversity, and inclusivity in all of our operations. This journal is the official publication of the Utilitas Mathematica Academy, Canada. It enjoys a good reputation and popularity at the international level in terms of research papers and distribution worldwide.
This document provides definitions and formulas for calculating curl, divergence, and line integrals. It defines curl as the measure of rotation in a vector field and divergence as the measure of how a vector field spreads out from a point. Formulas are given for calculating curl, divergence, and line integrals over curves with respect to arc length, x, y, and vector fields. It also discusses properties of conservative and irrotational vector fields as they relate to these calculations.
I am Steven M. I am a Maths Assignment Expert at mathsassignmenthelp.com. I hold a Master's in Mathematics from Ryerson University. I have been helping students with their assignments for the past 10 years. I solve assignments related to Maths.
Visit mathsassignmenthelp.com or email info@mathsassignmenthelp.com.
You can also call +1 678 648 4277 for any assistance with Maths Assignments.
I am Britney. I am a Differential Equations Assignment Solver at mathhomeworksolver.com. I hold a Master's in Mathematics, from London, UK. I have been helping students with their assignments for the past 10 years. I solved assignments related to Differential Equations Assignment.
Visit mathhomeworksolver.com or email support@mathhomeworksolver.com. You can also call on +1 678 648 4277 for any assistance with Differential Equations Assignment.
This document discusses the geometrical parameters and aerodynamic characteristics of fuselage bodies of revolution. It defines key parameters such as fuselage length, maximum diameter, aspect ratio, and nose and tail tapering. It describes three flow modes around bodies of revolution: attached flow at low angles of attack, separated flow at moderate angles, and non-symmetric vortex shedding at high angles. It provides equations for calculating aerodynamic forces and moments on a body of revolution based on surface pressure distribution.
The Mean Value Theorem is the most important theorem in calculus. It is the first theorem which allows us to infer information about a function from information about its derivative. From the MVT we can derive tests for the monotonicity (increase or decrease) and concavity of a function.
This document is the cover page for a mathematics preliminary examination. It provides instructions for candidates taking the exam, including writing their identification information, answering all questions, showing necessary work, using calculators appropriately, and specifying the degree of accuracy for answers. It also lists several mathematical formulas that may be useful for the exam, such as formulas for compound interest, mensuration, trigonometry, and statistics. The total number of marks for the exam is 80.
(1) The document is an examination paper for Secondary 4/5 students in mathematics. It consists of 13 printed pages containing 11 questions testing various math concepts.
(2) Instructions are provided for candidates, including writing their name, working clearly, using calculators where appropriate, and expressing some answers to a given degree of accuracy or in terms of pi.
(3) The exam covers topics like algebra, trigonometry, geometry, calculus, statistics, and financial mathematics. Questions involve factorizing expressions, solving equations, using circle properties, graphing functions, and probability.
The document discusses properties and equations of circles, including the standard form of a circle equation with a given center and radius. It also discusses tangent lines to circles, providing the process and equations for finding the equation of a tangent line to a circle at a given
The document describes Lagrange multipliers, which are used to find the extrema (maximum and minimum points) of a function subject to a constraint. Specifically:
1) A function z=f(x,y) defines a surface, and an equation g(x,y)=0 defines a curve on the xy-plane.
2) The points where this curve intersects the surface form a "trail".
3) The extrema on this trail occur where the gradients of the surface and constraint are parallel (or equivalently where their normals are parallel), allowing the use of Lagrange multipliers to solve the constrained optimization problem.
The document discusses tangent planes to surfaces. A surface is differentiable at a point if it is smooth and has a well-defined tangent plane at that point. The tangent plane approximates the surface near the point of tangency. To find the equation of the tangent plane, we calculate the partial derivatives of the surface function at the point to determine the slopes in the x- and y-directions. These slopes and the point define vectors in the tangent plane, and their cross product gives the normal vector. The equation of the tangent plane is then (z - c) = M(x - a) + L(y - b), where M and L are the partial derivatives and (a, b, c) is the
The document discusses parabolas and their key properties. It defines a parabola as the set of all points equidistant from a fixed point (the focus) and a line (the directrix). The line perpendicular to the directrix through the focus is called the axis. The point where the parabola intersects the axis is the vertex. Parabolas have reflecting properties such that light rays entering parallel to the axis will exit through the focus. This allows parabolic dishes to focus collected radio waves or light at a single point. The document also provides examples of graphing parabolas and finding their equations based on given properties, as well as calculating dimensions of the Hubble Space Telescope's parabolic mirror.
1. The document discusses techniques for finding extrema of functions, including absolute and local extrema. Critical points, endpoints, and the first and second derivative tests are covered.
2. The mean value theorem and Rolle's theorem are summarized. The mean value theorem relates the average and instantaneous rates of change over an interval.
3. Optimization problems can be solved by setting the derivative of the objective function equal to zero to find critical points corresponding to maxima or minima.
4. Newton's method is presented as an iterative process for approximating solutions to equations, using tangent lines to generate a sequence of improving approximations.
5. Anti-derivatives are defined as functions whose derivatives are a given
The document discusses graphs in polar coordinates. It begins by reviewing how polar coordinates (r, θ) represent a point P, where r is the distance from the origin and θ is the angle relative to the x-axis. It then discusses how to convert between rectangular (x, y) and polar (r, θ) coordinates. The document explains that polar equations relate r and θ, giving the example of r = θ which graphs as an Archimedean spiral. It also discusses the graphs of constant equations like r = c, which is a circle, and θ = c, which is a line. The document concludes by explaining how to graph other polar equations by plotting points.
This document is a chapter from an introductory mathematical analysis textbook. It covers curve sketching, including how to find relative and absolute extrema, determine concavity, use the second derivative test, identify asymptotes, and apply concepts of maxima and minima. The chapter contains learning objectives, an outline of topics, examples of applying techniques to sketch curves and solve optimization problems, and instructional content to introduce these curve sketching concepts.
The document describes how the Smith Chart maps impedances on the normalized complex impedance plane to the complex Γ plane. Vertical lines on the impedance plane representing constant resistance values r map to circles on the Γ plane, with centers located along the Γi = 0 line. Horizontal lines representing constant reactance values x also map to circles, with centers located along the Γr = 1 line. By mapping many such lines, the rectilinear grid of the impedance plane is distorted into the curvilinear grid of circles that make up the Smith Chart.
The document discusses the Smith chart, a graphical method for analyzing transmission lines. It provides advantages of using the Smith chart such as facilitating complex number calculations and visualizing transmission line systems. The basics of the Smith chart are outlined, including key reference points and how to plot complex impedances, move along the chart, and solve problems involving impedance matching. Several examples are worked through demonstrating using the Smith chart to find input impedance, reflection coefficient, and VSWR for different transmission line scenarios.
The Smith Chart provides a graphical tool for analyzing transmission lines and impedance matching circuits. It maps the reflection coefficient Γ onto a two-dimensional plane defined by the magnitude and phase of Γ. Transformations of Γ along a transmission line correspond to moving along a circular arc on the Smith Chart, allowing problems involving transmission line impedance transformations to be solved graphically. Special cases like quarter-wave and half-wave transmission lines correspond to rotations of 90 and 180 degrees on the Smith Chart.
This document introduces graph C*-algebras and related concepts:
- A graph C*-algebra is generated by partial isometries and projections representing a directed graph.
- A Cuntz-Krieger E-family satisfies relations involving these operators to represent a graph as bounded operators on a Hilbert space.
- The graph C*-algebra is then the closed algebra generated by this family of operators.
Intuitionistic First-Order Logic: Categorical semantics via the Curry-Howard ...Marco Benini
A novel approach to giving an interpretation of logic inside category theory. This work has been developed as part of my sabbatical Marie Curie fellowship in Leeds.
Presented at the Logic Seminar, School of Mathematics, University of Leeds (2012).
This document contains the questions and solutions from the First Semester B.E. Degree Examination in Engineering Mathematics from January 2013. It includes 10 multiple choice questions testing concepts in calculus, differential equations, and linear algebra. It also contains 4 full problems to solve related to derivatives, integrals, differential equations, and vectors/matrices.
The document discusses multi-variable functions and how to visualize them. It defines Rn as the set of n-tuples of real numbers. A n-variable real valued function maps from Rn to the real numbers. Level curves are used to visualize functions of two variables by setting z equal to constants and plotting the resulting equations in the x-y plane. This produces families of curves that depict the shape of the surface. Examples show how different functions produce different level curve shapes like ellipses, hyperbolas or parabolas.
The leadership of the Utilitas Mathematica Journal commits to strengthening our professional community by making it more just, equitable, diverse, and inclusive. We affirm that our mission, Promote the Practice and Profession of Statistics, can be realized only by fully embracing justice, equity, diversity, and inclusivity in all of our operations. This journal is the official publication of the Utilitas Mathematica Academy, Canada. It enjoys a good reputation and popularity at the international level in terms of research papers and distribution worldwide.
This document provides definitions and formulas for calculating curl, divergence, and line integrals. It defines curl as the measure of rotation in a vector field and divergence as the measure of how a vector field spreads out from a point. Formulas are given for calculating curl, divergence, and line integrals over curves with respect to arc length, x, y, and vector fields. It also discusses properties of conservative and irrotational vector fields as they relate to these calculations.
I am Steven M. I am a Maths Assignment Expert at mathsassignmenthelp.com. I hold a Master's in Mathematics from Ryerson University. I have been helping students with their assignments for the past 10 years. I solve assignments related to Maths.
Visit mathsassignmenthelp.com or email info@mathsassignmenthelp.com.
You can also call +1 678 648 4277 for any assistance with Maths Assignments.
I am Britney. I am a Differential Equations Assignment Solver at mathhomeworksolver.com. I hold a Master's in Mathematics, from London, UK. I have been helping students with their assignments for the past 10 years. I solved assignments related to Differential Equations Assignment.
Visit mathhomeworksolver.com or email support@mathhomeworksolver.com. You can also call on +1 678 648 4277 for any assistance with Differential Equations Assignment.
This document discusses the geometrical parameters and aerodynamic characteristics of fuselage bodies of revolution. It defines key parameters such as fuselage length, maximum diameter, aspect ratio, and nose and tail tapering. It describes three flow modes around bodies of revolution: attached flow at low angles of attack, separated flow at moderate angles, and non-symmetric vortex shedding at high angles. It provides equations for calculating aerodynamic forces and moments on a body of revolution based on surface pressure distribution.
The Mean Value Theorem is the most important theorem in calculus. It is the first theorem which allows us to infer information about a function from information about its derivative. From the MVT we can derive tests for the monotonicity (increase or decrease) and concavity of a function.
Problem Solving by Computer Finite Element MethodPeter Herbert
This document discusses using finite element methods and the cotangent Laplacian to solve partial differential equations numerically. It begins by explaining how to generate simplicial meshes by dividing a region into basic pieces. It then introduces the cotangent Laplacian, which approximates the Laplacian operator, and how it is calculated based on angles in triangles. Finally, it demonstrates applying the cotangent Laplacian to solve sample Dirichlet and Neumann boundary value problems and compares the approximate solutions to exact solutions, showing convergence as the mesh is refined.
This document discusses the mean value theorem and continuity in calculus. It defines Rolle's theorem, which states that if a function is continuous on a closed interval and differentiable on the open interval, and if the function is equal at the endpoints, then its derivative must be equal to zero for at least one value between the endpoints. It then uses Rolle's theorem to prove the mean value theorem, which states that the rate of change of a function over an interval is equal to the derivative of the function at some value between the endpoints. Finally, it introduces the Cauchy mean value theorem, which relates the rates of change of two functions over an interval to their derivatives at some interior point.
Jam 2006 Test Papers Mathematical Statisticsashu29
1. The document provides special instructions and useful data for a mathematical statistics test paper, including definitions, properties, and distributions.
2. It notes the test contains three sections - a compulsory section with objective and subjective questions, and two optional sections with only subjective questions on either mathematics or statistics.
3. Candidates must attempt the compulsory section and only one of the two optional sections, depending on their intended program of study. The questions cover topics like probability, random variables, distributions, and linear algebra.
The document discusses Legendre polynomials, which are special functions that arise in solutions to Laplace's equation in spherical coordinates. Some key points:
1) Legendre polynomials Pn(cosθ) are a set of orthogonal polynomials that satisfy Legendre's differential equation.
2) Pn(cosθ) can be defined using a generating function or by taking partial derivatives of 1/r.
3) Important properties of Legendre polynomials include P0(t)=1, Pn(1)=1, Pn(-1)=(-1)n, and a recurrence relation involving Pn+1, Pn, and their derivatives.
The document defines the operators curl and divergence for vector fields. Curl is defined as the cross product of del (the gradient operator) with the vector field and results in another vector. Divergence is defined as the dot product of del with the vector field and results in a scalar. Several examples of computing curl and divergence are worked out. Green's theorem, which relates line integrals of vector fields to surface integrals of curl and divergence, is also discussed.
This document introduces complex integration and provides examples of evaluating integrals along paths in the complex plane. It expresses integrals in terms of real and imaginary parts involving line integrals of functions. Key points made include:
- Complex integrals can be interpreted as line integrals over paths in the complex plane.
- Integrals of analytic functions over closed paths, like the unit circle, may yield simple results like 2πi or 0.
- Blasius' theorem relates forces and moments on a cylinder in fluid flow to complex integrals around the cylinder boundary.
8.further calculus Further Mathematics Zimbabwe Zimsec Cambridgealproelearning
This document discusses techniques for approximating integrals, including the trapezium rule and Simpson's rule. The trapezium rule approximates the area under a curve as the sum of trapezoidal areas formed by the function values at the endpoints of subintervals. Simpson's rule approximates the area as the sum of triangular areas, weighted differently for even and odd terms, formed by the function values at three evenly spaced points in each subinterval. Examples are given to demonstrate applying these rules to approximate definite integrals. The Simpson's rule is generally more accurate because it approximates the curve by a quadratic rather than a straight line as in the trapezium rule.
A New Polynomial-Time Algorithm for Linear ProgrammingSSA KPI
This document summarizes a new polynomial-time algorithm for linear programming.
1) The algorithm reduces the general linear programming problem to a canonical form and solves it through repeated application of projective transformations and optimization over spheres.
2) Each projective transformation followed by optimization reduces the objective function value by a constant factor, allowing the optimal solution to be found in polynomial time.
3) The algorithm runs in O(n3.5L0.5lnLlnlnL) time, an improvement over the ellipsoid method's O(n6L2lnLlnlnL) time.
This document discusses nonstationary covariance modeling. It begins by introducing concepts of covariance, correlation, and how correlation affects estimation and prediction. It then discusses properties of random fields like second-order stationarity and intrinsic stationarity. The difference between these two is explained. Common parametric models for isotropic covariance and variogram functions are presented, including spherical, exponential, Gaussian, rational quadratic, and Matérn models. Parameters and properties of these models like range, smoothness, and valid dimensionality are described. Examples of each model type are shown graphically.
This document discusses line integrals and Green's theorem. It defines line integrals as integrals of scalar or vector fields along a curve, parameterized by arc length. Line integrals may depend on the path taken between two points, but are path-independent for conservative vector fields. Green's theorem relates line integrals around a closed curve to a double integral over the enclosed region, equating the line integral to the curl of the vector field integrated over the region. An example demonstrates using Green's theorem to evaluate a line integral as a double integral.
1. Prove that the function f(x) = x^2 if x is rational, 0 otherwise, is differentiable at 0 but discontinuous everywhere else.
2. Use the Chain Rule to find an expression for the derivative of the inverse function g(f(c)) in terms of f'(c), given that f and g are inverse bijective functions between intervals with f differentiable at c and f(c) = 0, and g differentiable at f(c).
3. Prove several rules for derivatives, including the Power Rule and derivatives of composite functions.
This document discusses canonical-Laplace transforms and various testing function spaces. It begins by defining the canonical-Laplace transform and establishes some testing function spaces using Gelfand-Shilov technique, including CLa,b,γ, CLab,β, CLγa,b,β, CLa,b,β,n, and CLγa,,m,β,n. It then presents results on countable unions of s-type spaces, proving that various spaces can be expressed as countable unions and discussing topological properties. The document concludes by stating that canonical-Laplace transforms are generalized in a distributional sense and results on countable unions of s-type spaces are discussed, along with the topological structure
This document discusses the features of wing flow at subsonic speeds (M∞ < 1). For unswept high-aspect ratio wings, the flow features are determined by overflow from the lower surface to the upper surface at the wing tips, creating a spanwise flow. This induces a downwash behind the wing and results in induced drag. For optimum wings, the circulation distribution should follow an elliptical law to minimize induced drag. For swept wings, there is an additional curvature of flow lines caused by spanwise flow, affecting pressure distribution across the wing.
The document discusses the aerodynamic properties and geometry of aircraft wings. It describes how wings are formed by airfoils and outlines several key airfoil parameters like chord, thickness, camber, and their ratios. It also discusses wing planform characteristics such as span, taper ratio, sweep, and mean aerodynamic chord. Proper selection of wing geometry parameters like aspect ratio, taper, and twist can optimize an aircraft's aerodynamic qualities including drag, stability, and load distribution.
This document discusses the aerodynamic characteristics of wings in subsonic gas flow. It begins by introducing the linearized equation of gas dynamics that governs subsonic potential flow. It then transforms the coordinates to model an equivalent incompressible flow. Aerodynamic characteristics like lift, drag and pitching moment coefficients are shown to relate to the characteristics of the transformed wing based on this coordinate transformation. Expressions for these coefficients are derived, focusing on high aspect ratio wings. Factors like wing geometry, angle of attack and Mach number affect the coefficients.
1) The document discusses the aerodynamic characteristics of wings in supersonic gas flow, focusing on rectangular, triangular wings with subsonic or supersonic leading edges.
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Theme 4
1. SECTION 1. AERODYNAMICS OF LIFTING SURFACES
THEME 4. THE AERODYNAMIC CHARACTERISTICS OF
WINGS IN A FLOW OF INCOMPRESSIBLE FLUID
The main aerodynamic characteristics of an aircraft moving with Mach numbers
( M ∞ ≤ 0 .4 ) are considered in this lecture.
4.1. Wing lift coefficient
4.1.1. High-aspect-ratio wings
The dependence C ya = f ( α ) is linear on the segment of the attached flow (Fig.
4.1).
In general C ya = C α (α − α0 ) .
ya (4.1)
The angle of zero lift α0 is determined by the airfoil shape and wing twist. For a
flat wing
α 0 = −60 f ⎡ 1 + 10( x f − 0 ,2) ⎤ , degree.
0 2
⎢ ⎥ (4.2)
⎣ ⎦
Geometrical twist of the wing ϕ ( z )
causes changing of α0 by the value Δα0 ,
which can be approximately estimated for the
unswept wing by the formula
l
2
2
Δα 0 = −
S ∫ ϕ ( z) b( z) dz .
0
If the wing is swept then the absolute
value of Δα0 should be reduced by size
Fig. 4.1. Dependence of the lift 0 .0055 sin χ 0 .25 .
coefficient on the angle of attack
THEME 4 10/5/2008 31
2. The derivative C α depends on aspect ratio λ and the sweep angle χ , influence of
ya
taper η on derivative size is weak. The derivative C α does not depend on wing twist.
ya
It is possible to offer the following approximate formula for calculation of value of
Cα :
ya
πλ λ
Cα =
ya , m= (4.3)
α
1+τ + (1 + τ ) 2
+ ( π m)
2 C ya∞ cos χ 0 .5
Here the parameter τ takes into account the wing plan form and depends on η ,
λ , χ 0 .5 . It is possible to assume in the first approximation τ ≈ 0 (in general
τ ≈ 0 ...0 ,24 ),
⎡ ⎤
2 1 ⎥.
τ = 0 ,17 m ⎢η + (4.4)
⎢
⎣ (5η + 1) ⎦
3⎥
Parameter C α
ya∞ is a derivative for the airfoil (wing with λ → ∞ ) and is
calculated by the formula
(
C α = 2π − 1,69 4 c = 2π 1 − 0 ,27 4 c .
ya∞ ) (4.5)
It follows from the formula, that at λ → ∞ C α = C α ∞ cos χ 0 .5 and if in
ya ya
addition χ 0 .5 = 0 , then C α = C α ∞ .
ya ya
It is also possible to use the following formula for calculation C α :
ya
α Cα ∞ λ
ya
C ya = . (4.6)
1 α
pλ + C ya∞
π
Here p is the ratio of half-perimeter of the wing outline in the plan to span (Fig.
4.2). The significance of the last formula is in its universality and capability to apply to
any plan forms and aspect ratios (it is especially useful for wings with curvilinear edges
or edges with fracture).
THEME 4 10/5/2008 32
3. It is possible to define parameter p for
a wing represented in fig. 4.2, by the formula
l1 + l2 + l3 + l4
p= , or in case of tapered
l
wing - by the formula
⎛ 1 1 ⎞ 2
p = 0 .5 ⎜ + ⎟+ .
⎝ cos χ п .к . cos χ з .к . ⎠ λ (η + 1)
Fig. 4.2.
Let's analyze the influence of wing
geometrical parameters on value C α .
ya
1. With increasing of wing aspect ratio
λ the derivative of a lift coefficient on the
angle of attack C α grows (at conditions of
ya
χ = 0 and λ → ∞ the value of a derivative
tends to the airfoil characteristic C α = C α ∞
ya ya
(Fig. 4.3).
Fig. 4.3.
2. With increasing of sweep angle at
half-line chord ( 0 .5 chord line χ 0 .5 ) the
derivative value C α decreases (Fig. 4.4). (It
ya
occurs due to effect of slipping, at condition
of λ → ∞ , the sweep angles on the leading
and trailing edges are identical
χ l .e .≈ χ t .e .= χ , C α = C α ∞ cos χ ).
ya ya
3. The sweep influence on derivative
C α value decreases with decreasing of
ya
Fig. 4.4.
aspect ratio λ (Fig. 4.5) (sweep practically
THEME 4 10/5/2008 33
4. does not influence on value of lift coefficient
derivative on the angle of attack C α at small
ya
values of aspect ratio λ ).
4. The wing taper η influences a little
onto the value of a derivative C α (refer to
ya
formula (4.4), parameter τ ).
Fig. 4.5.
4.1.2. Wings of small aspect ratio
It is necessary to take into account the non-linear effects which occur at flow
about wings of small aspect ratio in dependence of a lift coefficient on the angle of
attack C ya = f ( α ) (Fig. 4.6)
C ya = C ya line + ΔC ya
where C ya line = C α (α − α 0 ) .
ya
It is also possible to define values of
α 0 and C α by the formulae for large aspect
ya
ratio wings at λ ≥ 2 The value of derivative
can be determined by the formula
Fig. 4.6.
Cα = π λ
ya for a wing of extremely small
2
aspect ratio λ < 1 , and the angle of zero lift for the wing with unswept trailing edge is
( )
equal to an angle of the trailing edge deflection α 0 = f ′ x t .e . , z , where y = f ( x , z ) -
∂ f
equation of a surface of a wing, f ′ = , x t .e . is trailing edge coordinate.
∂x
THEME 4 10/5/2008 34
5. The non-linear additive can be calculated by the formula which is fair at any
Mach numbers (the linear theory of subsonic flow refers only to a linear part of the
dependence).
4C α
1 − M ∞ cos 2 χ l .e . ⋅ (α − α 0 )
ya 2 2
ΔC ya = (4.7)
πλ
At a supersonic leading edge ( M ∞ cos χ l .e . > 1 ) the non-linear additive
disappears and ΔC ya = 0 .
With decreasing of λ the derivative C α decreases, and the non-linear additive
ya
ΔC ya grows (Fig. 4.7, 4.8).
Fig. 4.7. Character of changing of the non- Fig. 4.8. Character of changing of the non-
linear additive ΔC ya linear additive ΔC ya
4.2. Maximum lift coefficient.
The maximum lift coefficient is connected with the appearance and development
of flow stalling from the upper wing surface near the trailing edge and depends on many
factors, first of all, on the characteristics of the airfoil ( c , f , x f , nose section shape),
wing plan form ( χ , η ), Reynolds number Re . The λ value does not practically
THEME 4 10/5/2008 35
6. influence onto C ya max for wings of large aspect ratio (Fig. 4.9), at that with χ
decreasing α st increases.
The influence of λ has an effect as follows for wings of small aspect ratio:
C ya max grows with λ growing from 0 up to λ ~ 1 ; and then decreases - with
increasing of λ . Small values of C ya max ( C ya max ≈ 1,0 ...1,1 ) and large values of α st
( α st ≈ 25 o ...40 o ) (fig. 4.10) are characteristic for wings with λ < 3 . A flow stalling
delays in the latter case caused by influence of vortex structures formed on the upper
wing surface.
Fig. 4.9. Dependence C ya = ( α ) for Fig. 4.10. Dependence C ya = ( α ) for
wings of large aspect ratio λ ≥ 4 . wings of small aspect ratio λ < 3
The properties behaviour of curve C ya (α ) in area α st depends on the nose
section shape. The presence of C ya max low values is characteristic for a wing with the
pointed airfoil nose section which do not depend on Reynolds numbers (Fig. 4.11). The
increasing of C ya max (up to certain values) is characteristic for a wing with the rounded
airfoil nose section at increase of Reynolds numbers (Fig. 4.12).
Approximately, value C ya max of large aspect ratio wing ( λ ≥ 4 ) can be
determined by the formula
THEME 4 10/5/2008 36
7. ⎛ 0 .49η + 0 .91 2 ⎞ ⎡ η+2 ⎤
C ya max = C ya max ∞ ⎜ 1 − sin χ 0 .25 ⎟ ≈ C ya max ∞ ⎢1 − sin2 χ 0 .25 ⎥ ,
⎝ η+1 ⎠ ⎢
⎣ 2(η + 1) ⎥
⎦
where C ya max ∞ is the maximum value of an airfoil lift coefficient;
for symmetrical airfoil C ya max ∞ ≈ 35 c exp − 8 c at Reynolds numbers Re ≤ 10 6 and
( )
C ya max ∞ ≈ 39 .3 c exp − 8 c th Re⋅ 10 − 6 at Re ≥ 10 6 .
Fig. 4.11. Dependence C ya = ( α ) for Fig. 4.12. Dependence C ya = ( α ) for
wings with a sharp leading edge wings with a classical airfoil
Number Re is the kinematic factor of similarity describing the ratio of inertial
and viscous forces:
VL
Re = , (4.8)
ϑ
Where V is the characteristic speed; L is the characteristic length; ϑ is the kinematic
factor of viscosity.
THEME 4 10/5/2008 37
8. 4.3. Induced drag.
It is a result of the appearance of a vortex sheet behind a wing, which keeping
demands energy equivalent to work of induced drag force. The computational formulae
for definition of C xi are described below.
4.3.1. Wings of large aspect ratio
The induced drag coefficient of a large aspect ratio wing is determined
C xi = C xi ϕ = 0 + ΔC xiϕ , (4.9)
Where C xi ϕ =0 is the induced drag of a flat wing; ΔC xiϕ is the additive to induced drag
caused by geometrical twist.
We have
1+δ 2 2 1+δ
C xi ϕ = 0 = C ya = AC ya , A = (4.10)
π ⋅λ π ⋅λ
Dependence of induced drag at small angles of attack is approximated by
parabola (Fig. 4.13). The induced drag decreases at increasing of wing aspect ratio λ .
The coefficient δ is determined by the wing plan form and shows to what extent
the distribution of aerodynamic loading differs from the elliptical law, for which δ = 0 .
Generally δ ≈ 0 ...0 .10 . The expression for C xi ϕ =0 is represented as
1 2 1
C xi ϕ = 0 = C ya lately, where e is Osvald number, e = .
πλe 1+δ
Value of ΔC xi ϕ in contrast to C xi ϕ =0 can not be equal to zero in general at
C ya = 0 (because for non-flat wing various wing cross-sections may have lift
coefficients not equal to zero C ya ≠ 0 at total C ya = 0 ).
General expression for ΔC xiϕ looks like this: ΔC xiϕ = BC ya + C , where,
2
B = к 1ϕ w , С = к0ϕ w , ϕ w is the twist angle of tip cross-section; the values of
coefficients к0 and к 1 are also undertaken from the diagrams depending on wing plan
geometry ( λ , χ , η ), and twist law.
THEME 4 10/5/2008 38
9. Fig. 4.14. shows the comparison between induced drag of a flat wing and wing
having twist.
Fig. 4.13. Induced drag of a flat wing Fig. 4.14. Induced drag of a flat wing and
wing with twist
4.3.2. Wings of small aspect ratio
For a geometrically flat wing it is possible to assume:
C xi ϕ = 0 = C ya ⋅ α . (4.11)
This expression can be received if it is assumed that the sucking force is not
realized on the wing leading edge. The formula can be transformed to the following
form if the non-linear additive is neglected ( ΔC ya = 0 ) we have:
C xiϕ = 0 = AC ya , A = 1 C α
2
ya (4.12)
In such form the formula is used in practice (it coincides with the formula for a
flat wing of large aspect ratio)
πλ 2
( For a wing of small aspect ratio λ < 1 , C α =
ya and A = ; comparing
2 πλ
1+δ
with a wing of large aspect ratio A = we shall notice that δ = 1 ).
π ⋅λ
THEME 4 10/5/2008 39
10. 4.4. Wing polar
Polar of the first type is called the dependence between coefficients of
aerodynamic lift and drag force C ya = f (C xa ) . As well as the induced drag coefficient
the polar depends on twist presence on a wing. Therefore we shall separately consider
polar for a flat wing and polar for a wing having twist, and we shall conduct the
qualitative analysis.
4.4.1. Flat wing.
Summing induced drag C xi with profile drag C xp , we shall receive expression
for polar:
2
C xa = C xp + C xi = C xp + AC ya . (4.13)
It can be assumed that the profile drag
C xp does not depend on a lift coefficient C ya
( )
C xp ≠ f C ya . In this case we shall write
2
down C xa = C x 0 + AC ya , where C x0 is the
wing drag coefficient at C ya = 0 (in this case
Fig. 4.15. Dependence of profile drag it coincides with C xp ). It is necessary to note
on lifting force
that in general the profile drag C xp changes
2
by C ya especially at large values of α or C ya , it is approximately proportional to C ya
(Fig. 4.15); in some cases this change is taken into account in parameter A :
2 2 ~ 2 2
C xa = C x0 + aC ya + AC ya = C x0 + AC ya = C x0 + AC ya , (4.14)
~ 1+δ 1+δ 1
Where A = A + a ; for high-aspect-ratio wings A = and a + = ,
πλ πλ π λ ef
THEME 4 10/5/2008 40
11. 0 .95 λ
λ ef = ).
1 + 0 .16 λ tgχ 0 .5
The last polar writing (4.14) is the most
general form, which is fair for any
aerodynamic shapes if not to decipher
parameters C x0 and A . Parameter A has the
name of a polar pull-off coefficient.
∂ C xa
Obviously, that in general A = . Wing
2
∂ C ya
profile drag C xp does not depend on λ and
polar for wings of various aspect ratio λ are
look like as it is shown on fig. 4.16. As it was
Fig. 4.16. Flat wing polar
spoken earlier, the induced drag decreases
with increasing of aspect ratio λ , and consequently the drag C xa for a wing of infinite
aspect ratio λ → ∞ (airfoil) will be equal to profile drag C xp or C x0 .
4.4.2. Non-planar wings (wings with geometrical twist).
A The general form of polar equation for a non-planar wing
2
C xa = C + BC ya + AC ya , where profile drag C xp and part of induced drag caused by
2
wing geometrical twist enter parameter C , i.e. C = C xp + к0 ϕ w . Parameter B is also
determined by wing twist B = к 1ϕ w . The polar pull-off coefficient does not depend on
wing twist.
Polar equation for a wing with geometrical twist is a square parabola with
displaced peak (Fig. 4.17). It is possible to write down
2
B2
C xa =C−
4A
⎛
+ A⎜ C ya +
⎝
B⎞
(
⎟ = C xa min + A C ya − C yam
2 A⎠
)2 , (4.15)
THEME 4 10/5/2008 41
12. B2 B
Where C xa min = C − ; C yam = − .
4A 2A
From comparison of polar for flat and non-planar wings (the Fig. 4.18) it is
possible to reveal the advantages of using of a non-planar wing:
1. At C ya > C 0 twisted wing drag is less than ΔC xa = C xa tw − C xa
ya flat <0
2. The maximum lift-to-drag ratio of a non-planar wing is higher
K max tw > K max flat . (The wing is staying non-planar at mechanization deflection but
K max tw < K max flat ).
Fig. 4.17. Polar for a wing having twist Fig. 4.18. Polar for a flat and non-planar
(for a non-planar wing) wings
In addition, due to geometrical twist it is possible to provide wing balancing
without increase of induced drag (non-planar wing is self-balanced). It is easy to see,
that the advantages of a non-planar wing are shown at condition of B < 0 . In this case
polar peak displaces upwards.
4.5. Lift-to-drag ratio.
The ratio of aerodynamic lift to the drag force obtained by dividing the lift by the
drag is called lift-to-drag ratio K :
THEME 4 10/5/2008 42
13. C ya
K= , (4.16)
C xa
The lift-to-drag ratio is one of the basic characteristics determining efficiency of
an airplane.
C ya
For a flat wing K = . (4.17)
2
C x0 + AC ya
Fig. 4.19 shows the dependence of
K = f ( C ya ) . The lift coefficient and angle of
attack at which maximum lift-to-drag ratio
K max is achieved is called as optimal and
designated as C ya opt and α opt .
Let's define maximum lift-to-drag ratio.
For this purpose we shall differentiate K by
C ya and from the condition
2
∂K C x 0 + AC ya − 2 AC ya
= =0
Fig. 4.19. Dependence K = f ( C ya ) ∂ C ya
( 2 2
C x0 + AC ya )
we shall define values C ya at which the lift-to-drag ratio has extremes:
C x0
C ya opt = .
A
We shall receive the formula for calculation of maximum quality having
C x0
substituted C ya opt = in expression (4.17). We get
A
C x0
A 1
K max = ; K max = .
2 2 AC x 0
⎛ C x0 ⎞
C x0 + A⎜ ⎟
⎝ A ⎠
THEME 4 10/5/2008 43
14. The value of K max is increased with increasing of λ , decreasing of C x0 and δ
(δ = 0 for elliptical distribution of chordwise). We shall notice, that
1
K max ⋅ C ya opt = and does not depend on C x0 .
2A
C ya 1
For a non-planar wing - K = and K max = .
2 2 AC x 0 + B
C x0 + BC ya + AC ya
It is easy to find values of K max , C ya opt , α opt graphically. It follows from fig.
4.20 that it is necessary to conduct a beam tangent to polar from origin of coordinates to
search K max . The values of C ya and α in tangency point will correspond to C ya opt
and α opt .
Fig. 4.20. Dependencies C ya = f ( α ) , K = f ( α ) , C ya = f (C xa ) and connection
between them.
4.6. Distribution of aerodynamic loading along wing span.
Summarizing pressure distribution chordwise, we receive C ya се ÷ = f ( z ) .
Analysing the influence of wing geometrical parameters in planform on distribution of
THEME 4 10/5/2008 44
15. C ya cr .s .
aerodynamic loading spanwise it is convenient to use relative value C ya сr .s . = .
C ya
The function C ya cr .s . = f ( z) depends on λ , χ , η and geometrical twist (refer to
Fig. 3.5). Let's consider a flat wing. The influence of λ , χ , η is shown on the
following diagrams (Figs. 4.21, 4.22, 4.23).
Loading is distributed spanwise more regular with increasing of aspect ratio λ
.At λ = ∞ and for an elliptical wing C ya се ÷ = 1,0 . Refer to fig. 4.21.
The increasing of sweep angle χ causes growth of loading in a tip part and
reduction in root cross-section for a swept-back wing ( χ > 0 ). Refer to fig. 4.22.
The influence of wing taper η is similar to sweep χ effect : there is loading
growth in wing tip cross-sections with taper η increasing. Refer to fig. 4.23.
Distribution of lift along wing span:
Fig. 4.21. Depending on Fig. 4.22. Depending on Fig. 4.23. Depending on
aspect ratio at condition of sweep at condition of taper at condition of
χ = 0 , η = const = 1 λ = const , η = const λ = const , χ = 0
It is possible to write down approximately for a one-profile flat high-aspect-ratio
wing:
THEME 4 10/5/2008 45
16. ⎡ Cα ∞ ⎤ 1− z
2
2 ⎛
( 3 + τ )⎥ ⎜ 1 − cos χ 1 ⎞ ( 1 − z ) ; 0 ≤ z ≤ 1 ,
ya
C ya cr .s . = ⎢ 1 + − ⎟
⎢ πλ ⎥ 3μ + 1 − z 2 b( z ) ⎝ 4⎠
⎣ ⎦
Cα ∞
b( z ) , C α ∞ = 2π − 1,69 4 c , the values of parameter τ = f (λ , χ , η )
ya
Where μ = ya
4λ
are taken from the reference book or calculated.
Chords are distributed spanwise for a tapered wing with straight-line edges as
η − (η − 1) z
follows: b( z ) = 2 .
η+1
⎡ ⎤
⎢η 2 + 1 ⎥, m = λ 1
Approximately τ = 0 .17 m ,η= .
⎢
(5η + 1) 3 ⎥ C α ∞ cos χ 0 .5
ya
η
⎣ ⎦
4.7. Flow stalling.
Different values of C ya cr .s . along wing span are the reason of flow stalling in one
of cross-sections in which the local value C ya max cr .s . is reached. For example, the flow
stalling on a flat rectangular wing occurs at increasing of angles of attack in central
cross-section. It is evidently shown in fig. 4.24., that the true angle of attack in central
cross-section of a rectangular wing is more than at the tip α real 1 > α real 2 , therefore
flow stalling will begin in that place, where the true angle of attack comes nearer to
critical.
Fig. 4.24.
THEME 4 10/5/2008 46
17. In general the position of flow stalling spanwise on a tapered unswept wing can
be determined by the formula z stall ≈ 1 − η , for swept tapered wing the position of
stalling spanwise is determined by the following dependence
1−η + a ( 1 + a ) 2 − (1 − η ) 2
z stall ≈ , a = π η (1 − cos χ 0 .25 ) .
1 + a2
For improvement of wing aerodynamics at high angles of attack it is necessary to
create a condition of simultaneous flow stalling spanwise, i.e. uniform distribution of
loading spanwise It can be achieved by geometrical twist application. It is necessary to
apply wash-in to rectangular wing for the purpose of increasing loading in tip cross-
sections, wash-out is used for unswept wing, in this case tip cross-sections are unload.
(It has be noticed, that for a wing with the elliptical law of chords distribution spanwise
without geometrical twist all cross-sections have an identical C ya cr .s . , because
Vi = const and real angles of attack α real = const are identical for such wing
spanwise).
THEME 4 10/5/2008 47