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...
| Main Authors: | , , , |
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| Format: | Conference or Workshop Item |
| Language: | English |
| Published: |
Institute of Physics Publishing
2018
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| Subjects: | |
| 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 |
| Summary: | 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 |
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