Determination  Of  Pressure Distribution Around Aircraft’ Awing By Using Three Dimensional Low Order Panel Method

Sharfi, Omkalthom Yassen; Supervisor - Alkhawad

dc.contributor.author	Sharfi, Omkalthom Yassen
dc.contributor.author	Supervisor - Alkhawad
dc.date.accessioned	2014-10-26T12:41:07Z
dc.date.available	2014-10-26T12:41:07Z
dc.date.issued	2005-07-10
dc.identifier.citation	Sharfi,Omkalthom Yassen. Determination Of Pressure Distribution Around Aircraft’ Awing By Using Three Dimensional Low Order Panel Method /Omkalthom Yassen Sharfi;Alkhawad .-khartoum: Sudan university Of Sciences & Technology,College of Engineering,2005.-95p.:ill;28cm.-M.Sc.	en_US
dc.identifier.uri	http://repository.sustech.edu/handle/123456789/7518
dc.description	thesis	en_US
dc.description.abstract	This research a low order surface singularity distribution method (panel method) was used to analysis of L39 Aircraft Wing .A computer program was built to predict the influence coefficient matrices by assuming constant source and doublet distribution and applying the Dirichlet boundary condition. The value of the constant source was assumed and, with the influence matrices, the value of the constant doublet was predicted on each panel and wake. Tangential velocities were calculated giving the value of the pressure distribution. The required lift, drag &moment were then determined. The results were compared with the obtained computational results. This study give good results which was agreement with the standard figures in modern additional references.	en_US
dc.description.sponsorship	Sudan university Of Sciences & Technology	en_US
dc.language.iso	en	en_US
dc.publisher	Sudan university Of Sciences & Technology	en_US
dc.subject	Mechanical Engineer	en_US
dc.subject	Determination Of Pressure	en_US
dc.subject	Distribution Around Aircraft’	en_US
dc.title	Determination Of Pressure Distribution Around Aircraft’ Awing By Using Three Dimensional Low Order Panel Method	en_US
dc.type	Thesis	en_US