Computation of stability derivative for a wing for specific heat ratio= 1.66 for hypersonic flow

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Computation of stability derivative for a wing for specific heat ratio= 1.66 for hypersonic flow

The flight performance of aircraft relies on aerodynamic non-dimensional parameters like the drag coefficient, lift coefficient, and the moment coefficient of the aerospace vehicles. The knowledge of these properties is supremely necessary for optimal design, and thus the aerodynamics and the perfo...

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Bibliographic Details
Main Authors:	SHAMITHA, A, Crasta, Asha, Khan, Sher Afghan, VASAVI, P
Format:	Article
Language:	English
Published:	TJPRC Pvt. Ltd 2020
Subjects:	TL787 Astronautics
Online Access:	http://irep.iium.edu.my/80867/ http://irep.iium.edu.my/80867/1/22splissuejun2020ijmperd22j.pdf

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