Decambering: A numerical tool to predict post-stall aerodynamic data: Prediction of post-stall aerodynamic data for single and multiple wing configurations using airfoil data as input - Couverture souple

Mukherjee, Rinku

 
9783838302096: Decambering: A numerical tool to predict post-stall aerodynamic data: Prediction of post-stall aerodynamic data for single and multiple wing configurations using airfoil data as input
Couverture souple
ISBN 10 : 3838302095 ISBN 13 : 9783838302096
Editeur : LAP LAMBERT Academic Publishing, 2009

Synopsis

A novel scheme is presented for an iterative decambering approach to predict the post-stall characteristics of wings using known section data as inputs. The new scheme differs from earlier ones in the details of how the residual in the Newton iteration is computed. With earlier schemes, multiple solutions are obtained for wings at high angles of attack as the final converged solution depends on the initial conditions used for the iteration. With this scheme, multiple solutions at high angles of attack are brought to light right during the computation of the residuals for the Newton iteration. In general, the new scheme is found to be more robust at achieving convergence. Experimental validation is provided using experimental airfoil lift curves from Naik and Ostowari for three different aspect ratios of rectangular wings. Results are presented from a study of the stall characteristics of wings of different planform shapes and two configurations of a wing-tail and a wing-canard configuration. Results are also presented from a study to investigate possible asymmetric lift distributions when the iterations were started with an initial asymmetric distribution of the decambering.

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Présentation de l'éditeur

A novel scheme is presented for an iterative decambering approach to predict the post-stall characteristics of wings using known section data as inputs. The new scheme differs from earlier ones in the details of how the residual in the Newton iteration is computed. With earlier schemes, multiple solutions are obtained for wings at high angles of attack as the final converged solution depends on the initial conditions used for the iteration. With this scheme, multiple solutions at high angles of attack are brought to light right during the computation of the residuals for the Newton iteration. In general, the new scheme is found to be more robust at achieving convergence. Experimental validation is provided using experimental airfoil lift curves from Naik and Ostowari for three different aspect ratios of rectangular wings. Results are presented from a study of the stall characteristics of wings of different planform shapes and two configurations of a wing-tail and a wing-canard configuration. Results are also presented from a study to investigate possible asymmetric lift distributions when the iterations were started with an initial asymmetric distribution of the decambering.

Biographie de l'auteur

Rinku Mukherjee is an Assistant Professor in Applied Mechanics at IIT, Madras, India. Her academic profile includes BE (Civil Engg., Jadavpur University, 1998), MS (Ocean Engg. and Naval Architecture, IITKgp, 2001) and PhD (Aerospace Engg., NCSU, 2004). Her current research interests are in formation flight and unsteady and post-stall aerodynamics.

Les informations fournies dans la section « A propos du livre » peuvent faire référence à une autre édition de ce titre.

Éditeur
LAP LAMBERT Academic Publishing
Date d'édition
2009
Langue
anglais
ISBN 10 
3838302095
ISBN 13 
9783838302096
Reliure
Broché
Nombre de pages
108
Coordonnées du fabricant
non disponible
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