Numerical Computations of Transonic Critical Aerodynamic Behavior of a Realistic Artillery Projectile

The determination of aerodynamic coefficients by shell designers is a critical step in the development of any projectile design. Of particular interest is the determination of the aerodynamic coefficients at transonic speeds. It is in this speed regime that the critical aerodynamic behavior occurs...

Descripción completa

Guardado en:

Detalles Bibliográficos
Autor principal:	Ahmed F. M. Kridi
Formato:	article
Lenguaje:	EN
Publicado:	Al-Khwarizmi College of Engineering – University of Baghdad 2009
Materias:	Chemical engineering TP155-156 Engineering (General). Civil engineering (General) TA1-2040
Acceso en línea:	https://doaj.org/article/c581fd44eb9f45129d80c06ea752abfe
Etiquetas:	Agregar Etiqueta Sin Etiquetas, Sea el primero en etiquetar este registro!

id	oai:doaj.org-article:c581fd44eb9f45129d80c06ea752abfe
record_format	dspace
spelling	oai:doaj.org-article:c581fd44eb9f45129d80c06ea752abfe2021-12-02T03:14:35ZNumerical Computations of Transonic Critical Aerodynamic Behavior of a Realistic Artillery Projectile1818-11712312-0789https://doaj.org/article/c581fd44eb9f45129d80c06ea752abfe2009-03-01T00:00:00Zhttp://alkej.uobaghdad.edu.iq/index.php/alkej/article/view/518https://doaj.org/toc/1818-1171https://doaj.org/toc/2312-0789 The determination of aerodynamic coefficients by shell designers is a critical step in the development of any projectile design. Of particular interest is the determination of the aerodynamic coefficients at transonic speeds. It is in this speed regime that the critical aerodynamic behavior occurs and a rapid change in the aerodynamic coefficients is observed. Two-dimensional, transonic, flow field computations over projectiles have been made using Euler equations which were used for solution with no special treatment required. In this work a solution algorithm is based on finite difference MacCormack’s technique for solving mixed subsonic-supersonic flow problem. Details of the asymmetrically located shock waves on the projectiles have been determined. Computed surface pressures have been compared with experimental data and are found to be in good agreement. The pitching moment coefficient, determined from the computed flow fields, shows the critical aerodynamic behavior observed in free flights. Ahmed F. M. KridiAl-Khwarizmi College of Engineering – University of BaghdadarticleChemical engineeringTP155-156Engineering (General). Civil engineering (General)TA1-2040ENAl-Khawarizmi Engineering Journal, Vol 5, Iss 1 (2009)
institution	DOAJ
collection	DOAJ
language	EN
topic	Chemical engineering TP155-156 Engineering (General). Civil engineering (General) TA1-2040
spellingShingle	Chemical engineering TP155-156 Engineering (General). Civil engineering (General) TA1-2040 Ahmed F. M. Kridi Numerical Computations of Transonic Critical Aerodynamic Behavior of a Realistic Artillery Projectile
description	The determination of aerodynamic coefficients by shell designers is a critical step in the development of any projectile design. Of particular interest is the determination of the aerodynamic coefficients at transonic speeds. It is in this speed regime that the critical aerodynamic behavior occurs and a rapid change in the aerodynamic coefficients is observed. Two-dimensional, transonic, flow field computations over projectiles have been made using Euler equations which were used for solution with no special treatment required. In this work a solution algorithm is based on finite difference MacCormack’s technique for solving mixed subsonic-supersonic flow problem. Details of the asymmetrically located shock waves on the projectiles have been determined. Computed surface pressures have been compared with experimental data and are found to be in good agreement. The pitching moment coefficient, determined from the computed flow fields, shows the critical aerodynamic behavior observed in free flights.
format	article
author	Ahmed F. M. Kridi
author_facet	Ahmed F. M. Kridi
author_sort	Ahmed F. M. Kridi
title	Numerical Computations of Transonic Critical Aerodynamic Behavior of a Realistic Artillery Projectile
title_short	Numerical Computations of Transonic Critical Aerodynamic Behavior of a Realistic Artillery Projectile
title_full	Numerical Computations of Transonic Critical Aerodynamic Behavior of a Realistic Artillery Projectile
title_fullStr	Numerical Computations of Transonic Critical Aerodynamic Behavior of a Realistic Artillery Projectile
title_full_unstemmed	Numerical Computations of Transonic Critical Aerodynamic Behavior of a Realistic Artillery Projectile
title_sort	numerical computations of transonic critical aerodynamic behavior of a realistic artillery projectile
publisher	Al-Khwarizmi College of Engineering – University of Baghdad
publishDate	2009
url	https://doaj.org/article/c581fd44eb9f45129d80c06ea752abfe
work_keys_str_mv	AT ahmedfmkridi numericalcomputationsoftransoniccriticalaerodynamicbehaviorofarealisticartilleryprojectile
_version_	1718401882990313472

Numerical Computations of Transonic Critical Aerodynamic Behavior of a Realistic Artillery Projectile

Ejemplares similares