Computation of stability derivatives of an oscillating cone for specific heat ratio = 1.66
In this paper the expressions for stiffness and Damping derivatives are obtained in a closed form for perfect gas where the flow is quasi-steady and axi-axisymmetric, and the nose semi angle of the cone is such that the Mach number behind the shock . Results are presented for an oscillating cone...
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Institute of Physics Publishing
2018
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| Online Access: | http://irep.iium.edu.my/66482/ http://irep.iium.edu.my/66482/ http://irep.iium.edu.my/66482/1/66482_Computation%20of%20Stability%20Derivatives%20of%20an%20oscillating_article.pdf |
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iium-664822019-02-18T07:16:07Z http://irep.iium.edu.my/66482/ Computation of stability derivatives of an oscillating cone for specific heat ratio = 1.66 Shabana, Aysha Monis, Renita Sharon Crasta, Asha Khan, Sher Afghan TJ Mechanical engineering and machinery TJ255 Heat engines In this paper the expressions for stiffness and Damping derivatives are obtained in a closed form for perfect gas where the flow is quasi-steady and axi-axisymmetric, and the nose semi angle of the cone is such that the Mach number behind the shock . Results are presented for an oscillating cone for gas with , at different Mach numbers and semi cone angles. The Stiffness derivative decreases with pivot position and also with semi vertex angle, there is substantial change in the stiffness derivative when semi-vertex has been increased from 5 degrees to ten degrees, further increase in the semi-vertex angle results in marginal change in the stiffness derivative. Due the marginal change in the Mach number level there is marginal increase in the magnitude of the stability and with further increase in the inertia level the stability derivative conform to the Mach number independence principle. The present theory for Oscillating cone is restricted to quasi-steady case. Viscous effects have been neglected. The expressions so obtained for stability derivative in pitch are valid for a slender ogive which often approximates to the whole fuselage of an aircraft. Keywords: High Speed Flow, Hypersonic Flow, Oscillating cone, Stiffness derivative Institute of Physics Publishing 2018-06 Conference or Workshop Item PeerReviewed application/pdf en http://irep.iium.edu.my/66482/1/66482_Computation%20of%20Stability%20Derivatives%20of%20an%20oscillating_article.pdf Shabana, Aysha and Monis, Renita Sharon and Crasta, Asha and Khan, Sher Afghan (2018) Computation of stability derivatives of an oscillating cone for specific heat ratio = 1.66. In: 1st International Conference on Aerospace and Mechanical Engineering, AeroMech 2017, 21 - 22 November 2017, Parkroyal HotelBatu Ferringhi, Penang. http://iopscience.iop.org/article/10.1088/1757-899X/370/1/012059/meta |
| repository_type |
Digital Repository |
| institution_category |
Local University |
| institution |
International Islamic University Malaysia |
| building |
IIUM Repository |
| collection |
Online Access |
| language |
English |
| topic |
TJ Mechanical engineering and machinery TJ255 Heat engines |
| spellingShingle |
TJ Mechanical engineering and machinery TJ255 Heat engines Shabana, Aysha Monis, Renita Sharon Crasta, Asha Khan, Sher Afghan Computation of stability derivatives of an oscillating cone for specific heat ratio = 1.66 |
| description |
In this paper the expressions for stiffness and Damping derivatives are obtained in a
closed form for perfect gas where the flow is quasi-steady and axi-axisymmetric, and the nose
semi angle of the cone is such that the Mach number behind the shock . Results
are presented for an oscillating cone for gas with , at different Mach numbers and
semi cone angles. The Stiffness derivative decreases with pivot position and also with semi
vertex angle, there is substantial change in the stiffness derivative when semi-vertex has been
increased from 5 degrees to ten degrees, further increase in the semi-vertex angle results in
marginal change in the stiffness derivative. Due the marginal change in the Mach number level
there is marginal increase in the magnitude of the stability and with further increase in the
inertia level the stability derivative conform to the Mach number independence principle. The
present theory for Oscillating cone is restricted to quasi-steady case. Viscous effects have been
neglected. The expressions so obtained for stability derivative in pitch are valid for a slender
ogive which often approximates to the whole fuselage of an aircraft. Keywords: High Speed
Flow, Hypersonic Flow, Oscillating cone, Stiffness derivative |
| format |
Conference or Workshop Item |
| 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 |
Computation of stability derivatives of an oscillating cone for specific heat ratio = 1.66 |
| title_short |
Computation of stability derivatives of an oscillating cone for specific heat ratio = 1.66 |
| title_full |
Computation of stability derivatives of an oscillating cone for specific heat ratio = 1.66 |
| title_fullStr |
Computation of stability derivatives of an oscillating cone for specific heat ratio = 1.66 |
| title_full_unstemmed |
Computation of stability derivatives of an oscillating cone for specific heat ratio = 1.66 |
| title_sort |
computation of stability derivatives of an oscillating cone for specific heat ratio = 1.66 |
| publisher |
Institute of Physics Publishing |
| publishDate |
2018 |
| url |
http://irep.iium.edu.my/66482/ http://irep.iium.edu.my/66482/ http://irep.iium.edu.my/66482/1/66482_Computation%20of%20Stability%20Derivatives%20of%20an%20oscillating_article.pdf |
| first_indexed |
2023-09-18T21:34:23Z |
| last_indexed |
2023-09-18T21:34:23Z |
| _version_ |
1777412723001262080 |