International Journal of Aerodynamics http://www.inderscience.com/browse/index.php?journalID=140&year=2012&vol=2&issue=1 Inderscience Publishers Ltd en-uk International Journal of Aerodynamics 1743-5447 1743-5455 © 2012 Inderscience Publishers Ltd editor@inderscience.com https://www.inderscience.com/images/files/coverImgs/ijad_scoverijad.jpg http://www.inderscience.com/browse/index.php?journalID=140&year=2012&vol=2&issue=1 http://www.inderscience.com/link.php?id=46564 A narrative on the writing of the theoretical aspects of Low-Speed Aerodynamics is presented. Emphasis is placed on material specifically generated for the text and drawn from the author's educational, teaching and research experience. The close relationship between the classical small-disturbance theories and the modern computational approach to the solution of the incompressible potential flow problem is highlighted. The key subject areas included in the discussion are thin-airfoil theory, exact solutions with complex variables, perturbation methods including matched asymptotic expansions, lifting-line theory and boundary-layer theory, a topic added in the second edition. Low-Speed Aerodynamics – the theoretical aspects
Allen Plotkin
International Journal of Aerodynamics, Vol. 2, No. 1 (2012) pp. 1 - 21
A narrative on the writing of the theoretical aspects of Low-Speed Aerodynamics is presented. Emphasis is placed on material specifically generated for the text and drawn from the author's educational, teaching and research experience. The close relationship between the classical small-disturbance theories and the modern computational approach to the solution of the incompressible potential flow problem is highlighted. The key subject areas included in the discussion are thin-airfoil theory, exact solutions with complex variables, perturbation methods including matched asymptotic expansions, lifting-line theory and boundary-layer theory, a topic added in the second edition.

]]> 10.1504/IJAD.2012.046564 International Journal of Aerodynamics, Vol. 2, No. 1 (2012) pp. 1 - 21 Allen Plotkin Department of Aerospace Engineering, San Diego State University, San Diego, CA 92182-1308, USA low speed aerodynamics thin airfoil theory lifting line theory boundary layer theory incompressible potential flow airfoils. 2012-04-23T23:20:50-05:00 2 1 1 21 2012-04-23T23:20:50-05:00 http://www.inderscience.com/link.php?id=46548 The unique thermal and mechanical properties exhibited by shape memory alloys (SMA) present exciting design possibilities in the field of aerospace engineering. When properly trained, SMA wires act as linear actuators which can be used to deflect the flap and control the flap angle in the wings of aircraft. In this paper, the aerodynamic characteristics of the airfoil structures are investigated on the following models using SMA wire actuator. 1) SMA controlled plain flap airfoil structure; 2) SMA controlled split flap airfoil structure. The primary objective is to design a simple high lift device using shape memory actuator in order to increase the lift force acting on the airfoil structure at specific air velocity and various angles of attack. Analysis of smart wing using shape memory alloy
M. Senthilkumar
International Journal of Aerodynamics, Vol. 2, No. 1 (2012) pp. 22 - 35
The unique thermal and mechanical properties exhibited by shape memory alloys (SMA) present exciting design possibilities in the field of aerospace engineering. When properly trained, SMA wires act as linear actuators which can be used to deflect the flap and control the flap angle in the wings of aircraft. In this paper, the aerodynamic characteristics of the airfoil structures are investigated on the following models using SMA wire actuator. 1) SMA controlled plain flap airfoil structure; 2) SMA controlled split flap airfoil structure. The primary objective is to design a simple high lift device using shape memory actuator in order to increase the lift force acting on the airfoil structure at specific air velocity and various angles of attack.

]]> 10.1504/IJAD.2012.046548 International Journal of Aerodynamics, Vol. 2, No. 1 (2012) pp. 22 - 35 M. Senthilkumar Department of Mechanical Engineering, PSG College of Technology, Coimbatore 641 004, India plain flaps split flaps shape memory alloys SMAs angle of attack high lift device smart wings aerospace engineering airfoils lift force air velocity areodynamics linear actuators. 2012-04-23T23:20:50-05:00 2 1 22 35 2012-04-23T23:20:50-05:00 http://www.inderscience.com/link.php?id=46554 The aerodynamic characteristics of bodies in ground effect conditions are an important consideration for road vehicle aerodynamic design and analysis. The particular geometric properties of two aerofoils in ground effect are investigated in this study, using two-dimensional computational fluid dynamics. By comparing the different flow features found for each of the two aerofoils, the important geometric components for optimised ground effect performance are determined. This information is then used to modify the shape of one of the aerofoils, with the aim of producing greater performance characteristics. The modified aerofoil is found to produce greater downforce (while also producing an increase in the drag force), which represents an improvement in the aerodynamic characteristics for this application. Variation of ground effect phenomena about downforce generating aerofoils caused by changes in aerofoil shape
Jonathan W. Vogt; Tracie J. Barber
International Journal of Aerodynamics, Vol. 2, No. 1 (2012) pp. 36 - 49
The aerodynamic characteristics of bodies in ground effect conditions are an important consideration for road vehicle aerodynamic design and analysis. The particular geometric properties of two aerofoils in ground effect are investigated in this study, using two-dimensional computational fluid dynamics. By comparing the different flow features found for each of the two aerofoils, the important geometric components for optimised ground effect performance are determined. This information is then used to modify the shape of one of the aerofoils, with the aim of producing greater performance characteristics. The modified aerofoil is found to produce greater downforce (while also producing an increase in the drag force), which represents an improvement in the aerodynamic characteristics for this application.

]]> 10.1504/IJAD.2012.046554 International Journal of Aerodynamics, Vol. 2, No. 1 (2012) pp. 36 - 49 Jonathan W. Vogt; Tracie J. Barber School of Mechanical and Manufacturing Engineering, University of New South Wales, Sydney, 2052, Australia. ' School of Mechanical and Manufacturing Engineering, University of New South Wales, Sydney, 2052, Australia ground effect aerodynamics automotive aerodynamics computational fluid dynamics CFD downforce inverted aerofoils airfoil shape vehicle design drag force. 2012-04-23T23:20:50-05:00 2 1 36 49 2012-04-23T23:20:50-05:00 http://www.inderscience.com/link.php?id=46539 In the present work, we study the aerodynamic effects of triangular vortex generators, as passive flow control devices, placed on the upper surface of an airfoil submitted to a low Reynolds number turbulent flow. In the experiments, different configurations of those devices have been studied. An Eppler 387 airfoil was used. The tests were performed in a turbulent boundary layer wind tunnel using a two component aerodynamic balance and flow visualisation systems. Turbulent flow characterisation was made by means of hot wire anemometry. Calculations of local turbulent intensity as well as temporal and spatial turbulent scales were made. Vortex generators were located at 10% and 20% of the airfoil chord from the leading edge, modifying its angle of incidence refereed to the free stream. The results show changes in the aerodynamic section coefficients, C<SUB align="right">1, C<SUB align="right">d and C<SUB align="right">1, for the different vortex generator configurations. Neither hysteresis effects, nor leading edge bubbles were found in the experiments. Experimental study of vortex generators effects on low Reynolds number airfoils in turbulent flow
Juan Sebastián Delnero; Julio Marañon Di Leo; Mauricio Ezequiel Camocardi; Mariano A. Martinez; Jorge L. Colman Lerner
International Journal of Aerodynamics, Vol. 2, No. 1 (2012) pp. 50 - 65
In the present work, we study the aerodynamic effects of triangular vortex generators, as passive flow control devices, placed on the upper surface of an airfoil submitted to a low Reynolds number turbulent flow. In the experiments, different configurations of those devices have been studied. An Eppler 387 airfoil was used. The tests were performed in a turbulent boundary layer wind tunnel using a two component aerodynamic balance and flow visualisation systems. Turbulent flow characterisation was made by means of hot wire anemometry. Calculations of local turbulent intensity as well as temporal and spatial turbulent scales were made. Vortex generators were located at 10% and 20% of the airfoil chord from the leading edge, modifying its angle of incidence refereed to the free stream. The results show changes in the aerodynamic section coefficients, C<SUB align="right">1, C<SUB align="right">d and C<SUB align="right">1, for the different vortex generator configurations. Neither hysteresis effects, nor leading edge bubbles were found in the experiments.

]]> 10.1504/IJAD.2012.046539 International Journal of Aerodynamics, Vol. 2, No. 1 (2012) pp. 50 - 65 Juan Sebastián Delnero; Julio Marañon Di Leo; Mauricio Ezequiel Camocardi; Mariano A. Martinez; Jorge L. Colman Lerner Laboratorio de Capa Límite y Fluidodinámica Ambiental, Facultad de Ingeniería, Universidad Nacional de La Plata, La Plata, Buenos Aires, 1900, Argentina; Consejo Nacional de Investigaciones Científicas y Técnicas, Avda. Rivadavia 1917, CP C1033AAJ, Cdad. de Buenos Aires, Argentina. ' Laboratorio de Capa Límite y Fluidodinámica Ambiental, Facultad de Ingeniería, Universidad Nacional de La Plata, La Plata, Buenos Aires, 1900, Argentina; Consejo Nacional de Investigaciones Científicas y Técnicas, Avda. Rivadavia 1917, CP C1033AAJ, Cdad. de Buenos Aires, Argentina. ' Laboratorio de Capa Límite y Fluidodinámica Ambiental, Facultad de Ingeniería, Universidad Nacional de La Plata, La Plata, Buenos Aires, 1900, Argentina; Consejo Nacional de Investigaciones Científicas y Técnicas, Avda. Rivadavia 1917, CP C1033AAJ, Cdad. de Buenos Aires, Argentina. ' Laboratorio de Capa Límite y Fluidodinámica Ambiental, Facultad de Ingeniería, Universidad Nacional de La Plata, La Plata, Buenos Aires, 1900, Argentina; Department of Aerospace Engineering, Politecnico di Torino, C.so Duca degli Abruzzi 24, Turin (10129), Italy. ' Laboratorio de Capa Límite y Fluidodinámica Ambiental, Facultad de Ingeniería, Universidad Nacional de La Plata, La Plata, Buenos Aires, 1900, Argentina turbulent flow low Reynolds numbers airfoils vortex generators aerodynamics passive flow control flow visualisation. 2012-04-23T23:20:50-05:00 2 1 50 65 2012-04-23T23:20:50-05:00 http://www.inderscience.com/link.php?id=46532 A pressure-based implicit procedure is due to solve Navier-Stokes equations. A non-orthogonal mesh with collocated finite volume formulation is used to simulate flow around the smart and conventional flaps of airfoil under the ground effect. Cantilever beam with uniformly varying load with roller support at the free end is considered for smart flaps. The boundedness criteria for this procedure are determined by a normalised variable diagram (NVD) scheme. The procedure incorporates the k-ε eddy-viscosity turbulence model. The method is first validated against experimental data. Then, the SIMPLE algorithm is applied for turbulent aerodynamic flows around airfoil with smart and conventional flaps for different attack angle, flap angle and ground clearance where the results of two flaps are compared. It is found that the pressure coefficient distribution in a smart flap is smoother than a conventional one. The comparisons show that the quality of the solution is considerable. Application of smart flap for race car wings
Mohamad Hassan Djavareshkian; Ali Esmaeli
International Journal of Aerodynamics, Vol. 2, No. 1 (2012) pp. 66 - 92
A pressure-based implicit procedure is due to solve Navier-Stokes equations. A non-orthogonal mesh with collocated finite volume formulation is used to simulate flow around the smart and conventional flaps of airfoil under the ground effect. Cantilever beam with uniformly varying load with roller support at the free end is considered for smart flaps. The boundedness criteria for this procedure are determined by a normalised variable diagram (NVD) scheme. The procedure incorporates the k-ε eddy-viscosity turbulence model. The method is first validated against experimental data. Then, the SIMPLE algorithm is applied for turbulent aerodynamic flows around airfoil with smart and conventional flaps for different attack angle, flap angle and ground clearance where the results of two flaps are compared. It is found that the pressure coefficient distribution in a smart flap is smoother than a conventional one. The comparisons show that the quality of the solution is considerable.

]]> 10.1504/IJAD.2012.046532 International Journal of Aerodynamics, Vol. 2, No. 1 (2012) pp. 66 - 92 Mohamad Hassan Djavareshkian; Ali Esmaeli Mechanical Engineering Department, Faculty of Engineering, Ferdowsi University of Mashhad, Mashhad, Iran. ' Mechanical Engineering Department, Faculty of Engineering, Ferdowsi University of Mashhad, Mashhad, Iran smart airfoils ground effect race car flaps aerodynamic coefficients race cars racing cars racing car wings flow simulation turbulence modelling aerodynamic flows vehicle aerodynamics. 2012-04-23T23:20:50-05:00 2 1 66 92 2012-04-23T23:20:50-05:00 http://www.inderscience.com/link.php?id=46562 A new undergraduate course in computational aerodynamics was developed several years ago that gives students experience with the modern computational tools of aerodynamics, primarily from an applications perspective. While introducing students to the important computational topics of accuracy and stability, the course stresses the practical tools that computational aerodynamics requires: importance of understanding the physical problem, developing a good grid, checking results for convergence and accuracy, understanding how to accurately simulate flows, and the importance of modern flow visualisation capabilities. A number of 'lessons learned' have resulted from teaching the course, which has led to an evolution of the course contents and software used. An updated description of the course contents and improvements to the course are provided, as well as samples of projects and tutorials used in the course. Provided appropriate attention and support is available, undergraduate students can learn computational aerodynamics at a level that will make them intelligent users of modern computational aerodynamics tools. Computational aerodynamics education at the US Air Force Academy
Russell M. Cummings
International Journal of Aerodynamics, Vol. 2, No. 1 (2012) pp. 93 - 109
A new undergraduate course in computational aerodynamics was developed several years ago that gives students experience with the modern computational tools of aerodynamics, primarily from an applications perspective. While introducing students to the important computational topics of accuracy and stability, the course stresses the practical tools that computational aerodynamics requires: importance of understanding the physical problem, developing a good grid, checking results for convergence and accuracy, understanding how to accurately simulate flows, and the importance of modern flow visualisation capabilities. A number of 'lessons learned' have resulted from teaching the course, which has led to an evolution of the course contents and software used. An updated description of the course contents and improvements to the course are provided, as well as samples of projects and tutorials used in the course. Provided appropriate attention and support is available, undergraduate students can learn computational aerodynamics at a level that will make them intelligent users of modern computational aerodynamics tools.

]]> 10.1504/IJAD.2012.046562 International Journal of Aerodynamics, Vol. 2, No. 1 (2012) pp. 93 - 109 Russell M. Cummings United States Air Force Academy, CO, 80840, USA computational fluid dynamics CFD computational aerodynamics higher education aerodynamics education flow visualisation. 2012-04-23T23:20:50-05:00 2 1 93 109 2012-04-23T23:20:50-05:00