Estimation of stiffness derivative of an ogive for specific heat ratio 1.666

This paper focusses attention on studying the effect of the flow medium on the aerodynamic characteristics of the ogive at significant inertia levels. Accordingly, the hypersonic similitude is used to find analytical expression to evaluate the pressure dissemination on the exterior of the ogive and...

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Main Authors:	Shabana, Aysha, Monis, Renita Sharon, Crasta, Asha, Khan, Sher Afghan
Format:	Article
Language:	English English
Published:	The Mattingley Publishing Co., Inc 2019
Subjects:	QA Mathematics QA297 Numerical Analysis
Online Access:	http://irep.iium.edu.my/77586/ http://irep.iium.edu.my/77586/ http://irep.iium.edu.my/77586/7/77586%20Estimation%20of%20Stiffness%20Derivative.pdf http://irep.iium.edu.my/77586/9/77586%20%20%20%20%20Estimation%20of%20Stiffness%20Derivative%20SCOPUS.pdf

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spelling	iium-775862020-01-10T08:19:06Z http://irep.iium.edu.my/77586/ Estimation of stiffness derivative of an ogive for specific heat ratio 1.666 Shabana, Aysha Monis, Renita Sharon Crasta, Asha Khan, Sher Afghan QA Mathematics QA297 Numerical Analysis This paper focusses attention on studying the effect of the flow medium on the aerodynamic characteristics of the ogive at significant inertia levels. Accordingly, the hypersonic similitude is used to find analytical expression to evaluate the pressure dissemination on the exterior of the ogive and hence, finally to get the stiffness derivatives for Mach quantities from the Mach number M = 5 to 15, and the stream ricochet directions in the range from 100 to 250. This study considers two values of the λ = 5, and 10 are for the ogival shape of the nose. The γ value considered is 1.666. Using this value of the specific heat ratio the expression for rigidityderived for an ogive through the assumption that the gas is in-viscid and ideal, the indication is semi-steady, and the front noseapproach of the ogive is to such an extent that the inertia level behindhand the tremor M2 after the shock M2 ≥ 2.5 . The consequencesdesignate that with the rise in the Mach number since M = 5 to M = 15, Initially the magnitude of the stiffness derivative and later with superfluousrise in the Mach (M), it befitsself-regulating of inertia level and Mach independence principle has revisited. When the λ = 10, there is a swing of the midpoint of force towards the leading edge. The Mattingley Publishing Co., Inc 2019-12 Article PeerReviewed application/pdf en http://irep.iium.edu.my/77586/7/77586%20Estimation%20of%20Stiffness%20Derivative.pdf application/pdf en http://irep.iium.edu.my/77586/9/77586%20%20%20%20%20Estimation%20of%20Stiffness%20Derivative%20SCOPUS.pdf Shabana, Aysha and Monis, Renita Sharon and Crasta, Asha and Khan, Sher Afghan (2019) Estimation of stiffness derivative of an ogive for specific heat ratio 1.666. Test Engineering and Management, 81 (11-12). pp. 5091-5100. ISSN 0193-4120 http://www.testmagzine.biz/index.php/testmagzine/article/view/710/635
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	QA Mathematics QA297 Numerical Analysis
spellingShingle	QA Mathematics QA297 Numerical Analysis Shabana, Aysha Monis, Renita Sharon Crasta, Asha Khan, Sher Afghan Estimation of stiffness derivative of an ogive for specific heat ratio 1.666
description	This paper focusses attention on studying the effect of the flow medium on the aerodynamic characteristics of the ogive at significant inertia levels. Accordingly, the hypersonic similitude is used to find analytical expression to evaluate the pressure dissemination on the exterior of the ogive and hence, finally to get the stiffness derivatives for Mach quantities from the Mach number M = 5 to 15, and the stream ricochet directions in the range from 100 to 250. This study considers two values of the λ = 5, and 10 are for the ogival shape of the nose. The γ value considered is 1.666. Using this value of the specific heat ratio the expression for rigidityderived for an ogive through the assumption that the gas is in-viscid and ideal, the indication is semi-steady, and the front noseapproach of the ogive is to such an extent that the inertia level behindhand the tremor M2 after the shock M2 ≥ 2.5 . The consequencesdesignate that with the rise in the Mach number since M = 5 to M = 15, Initially the magnitude of the stiffness derivative and later with superfluousrise in the Mach (M), it befitsself-regulating of inertia level and Mach independence principle has revisited. When the λ = 10, there is a swing of the midpoint of force towards the leading edge.
format	Article
author	Shabana, Aysha Monis, Renita Sharon Crasta, Asha Khan, Sher Afghan
author_facet	Shabana, Aysha Monis, Renita Sharon Crasta, Asha Khan, Sher Afghan
author_sort	Shabana, Aysha
title	Estimation of stiffness derivative of an ogive for specific heat ratio 1.666
title_short	Estimation of stiffness derivative of an ogive for specific heat ratio 1.666
title_full	Estimation of stiffness derivative of an ogive for specific heat ratio 1.666
title_fullStr	Estimation of stiffness derivative of an ogive for specific heat ratio 1.666
title_full_unstemmed	Estimation of stiffness derivative of an ogive for specific heat ratio 1.666
title_sort	estimation of stiffness derivative of an ogive for specific heat ratio 1.666
publisher	The Mattingley Publishing Co., Inc
publishDate	2019
url	http://irep.iium.edu.my/77586/ http://irep.iium.edu.my/77586/ http://irep.iium.edu.my/77586/7/77586%20Estimation%20of%20Stiffness%20Derivative.pdf http://irep.iium.edu.my/77586/9/77586%20%20%20%20%20Estimation%20of%20Stiffness%20Derivative%20SCOPUS.pdf
first_indexed	2023-09-18T21:49:26Z
last_indexed	2023-09-18T21:49:26Z
_version_	1777413669275041792

Estimation of stiffness derivative of an ogive for specific heat ratio 1.666

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