Theoretical and Computational Aerodynamics by Tapan Sengupta

Theoretical and Computational Aerodynamics by Tapan Sengupta

Aerodynamics has seen many developments due to the growth of scientific computing, which has caused the design cycle time of aerospace vehicles to be heavily reduced. Today computational aerodynamics appears in the preliminary step of a new design, relegating costly, time-consuming wind tunnel testing to the final stages of design. Theoretical and Computational Aerodynamics is aimed to be a comprehensive textbook, covering classical aerodynamic theories and recent applications made possible by computational aerodynamics. It starts with a discussion on lift and drag from an overall dynamical approach, and after stating the governing Navier-Stokes equation, covers potential flows and panel method. Low aspect ratio and delta wings (including vortex breakdown) are also discussed in detail, and after introducing boundary layer theory, computational aerodynamics is covered for DNS and LES. Other topics covered are on flow transition to analyse NLF airfoils, bypass transition, streamwise and cross-flow instability over swept wings, viscous transonic flow over airfoils, low Reynolds number aerodynamics, high lift devices and flow control. Key features: Blends classical theories of incompressible aerodynamics to panel methods Covers lifting surface theories and low aspect ratio wing and wing-body aerodynamics Presents computational aerodynamics from first principles for incompressible and compressible flows Covers unsteady and low Reynolds number aerodynamics Includes an up-to-date account of DNS of airfoil aerodynamics including flow transition for NLF airfoils Contains chapter problems and illustrative examples Accompanied by a website hosting problems and a solution manual Theoretical and Computational Aerodynamics is an ideal textbook for undergraduate and graduate students, and is also aimed to be a useful resource book on aerodynamics for researchers and practitioners in the research labs and the industry.

“The book ‘is aimed to be a comprehensive textbook’: the classical subject matter, including the transition and stability theory in Chapter 9, would be a useful addition to the literature of any undergraduate or graduate student; the computational sections contain little in terms of fundamentals of numerics but, accepting that useful computational results are the focus, results are presented for several applications that would be of interest to many aerodynamicists”  (The Aeronautical Journal, 3 February 2015)

Prof. Sengupta received his basic aeronautical/aerospace education from IIT Kharagpur, IISc Bangalore and Georgia Tech., Atlanta, USA. He has worked in various research organizations and educational institutes at NAL Bangalore, India; Univ. of Cambridge, U.K.; National University of Singapore, Singapore and IIT Kanpur, where he currently holds the PR Dwivedi Chair apart from leading HPCL, IIT Kanpur. His research interests span across fields of scientific and high performance computing; fundamental fluid mechanics and aerodynamics; transition and turbulence. His research teams have refined and expanded areas of scientific computing, HPC, receptivity/instability, transition and turbulence. His interests in fundamental aspects of aerodynamics have resulted in this book containing classical theoretical analyses and newer topics of transonic aerodynamics; natural laminar flow airfoil analysis and design; low Reynolds number aerodynamics; flow control to delay transition and separation. These later topics are outcome of his contributions in direct numerical simulation (DNS) and large eddy simulation (LES).

SKU	Nicht verfügbar
ISBN 13	9781118787595
ISBN 10	1118787595
Titel	Theoretical and Computational Aerodynamics
Autor	Tapan Sengupta
Serie	Aerospace Series
Buchzustand	Nicht verfügbar
Bindungsart	Hardback
Verlag	Wiley
Erscheinungsjahr	2014-11-17
Seitenanzahl	528
Hinweis auf dem Einband	Die Abbildung des Buches dient nur Illustrationszwecken, die tatsächliche Bindung, das Cover und die Auflage können sich davon unterscheiden.
Hinweis	Nicht verfügbar