By John D. Anderson

* bargains a readable, thorough review of easy aerodynamics, with a variety of discussions of aviation historical past and improvement
* comprises new assurance of the Computational Fluid Dynamics (CFD) and illustrations to assist clarify the fabric
* greater than a dozen "design boxes" draw the reader's recognition and illustrate the sensible functions

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Additional resources for Fundamentals of Aerodynamics (3rd Edition)

Example text

One purpose of this book is to provide the reader with the technical background necessary to fully understand the nature of such practical aerodynamic applications. 3 ROAD MAP FOR THIS CHAPTER When learning a new subject, it is important for you to know where you are, where you are going, and how you can get there. Therefore, at the beginning of each chapter in this book, a road map will be given to help guide you through the material of that chapter and to help you obtain a perspective as to how the material fits within the general framework of aerodynamics.

Along the base of the body, we assume that p = Poo. Neglecting the effect of friction, obtain an expression for the drag coefficient of the cone, where CD is based on the area of the base Sb. 17) here. 17 is a shape in three-dimensional space. Hence, we must treat this three-dimensional body as follows. 17 / / / \ I I / / / .......... 2. The total drag due to the pressure acting over the total surface area of the cone is rh D= lo 2rrrpdr- lrh 2rrp x dr 0 The first integral is the horizontal force on the inclined surface of the cone, and the second integral is the force on the base of the cone.

In contrast, as we will see later, the drag of a slender body at subsonic speed, where there is no shock wave, is mainly skin friction drag. The drag coefficient is obtained as follows. ) Note that, in the above, the standard sea level temperature of 288 K is used. 4 m/s. 16), integrating the pressure coefficients and skin friction coefficients to obtain directly the drag coefficient. 1054 Also, T =431s- . =~ -- = 02 Cfu . 513 X 1O- x- o. 022 I This is the same result as obtained earlier. 2 Consider a cone at zero angle of attack in a hypersonic flow.

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