Evaluation of Stiffness Derivative for a Delta wing with Straight Leading Edges in Unsteady Flow
Renita Sharon Monis1, Asha Crasta2, S.A. Khan3
1Renita Sharon Monis, Assistant Professor Sr, SMVITM, Bantakal & Research Scholar, MITE, Moodbidri, Mangalore (Karnataka), India.
2Asha Crasta, Assosciate Professor, MITE, Moodbidri, Mnagalore (Karnataka), India.
3S.A. Khan, Department of Mechanical Engineering, International Islamic University, Kuala Lumpur Malaysia.
Manuscript received on 29 May 2019 | Revised Manuscript received on 11 June 2019 | Manuscript Published on 22 June 2019 | PP: 754-762 | Volume-8 Issue-3S, February 2019 | Retrieval Number: C11610283S19/19©BEIESP
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: The emphasis of this paper is to examine the Stiffness derivative variation with the pivot position by varying Mach number in unsteady flow and its comparison with quasi-steady flow of Crasta & Khan for varying angle of attack with different Mach number. From the results, it is evident that Stiffness derivative decreases as the Mach number increases. Comparison with Liu as well as Crasta & Khan theory it is evident that there is an improvement in the present theory being unsteady over quasi-steady theory, in addition to the fact that in the present work the pressure on the leeward surface is taken into account which results in increased value of the stability derivative and the same is clearly visible in results.
Keywords: Delta Wing, Hypersonic, Straight Leading Edge, Unsteady.
Scope of the Article: Mechanical Maintenance