THERMAL SCIENCE

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Dejan P. Ninković

THERMAL AND AERODYNAMIC PERFORMANCES OF THE SUPERSONIC MOTION

ABSTRACT
Generally speaking, Mach number of 4 can be taken as a boundary value for transition from conditions for supersonic, into the area of hypersonic flow, distinguishing two areas: area of supersonic in which the effects of the aerodynamic heating can be neglected and the area of hypersonic, in which the thermal effects become dominant. This paper presents the effects in static and dynamic areas, as well as presentation of G.R.O.M. software for determination of the values of aerodynamic derivatives, which was developed on the basis of linearized theory of supersonic flow. Validation of developed software was carried out through different types of testing, proving its usefulness for engineering practice in the area of supersonic wing aerodynamic loading calculations, even at high Mach numbers, with dominant thermal effects.
KEYWORDS
distribution of circulation, perturbation velocity potential, aerodynamic derivatives
PAPER SUBMITTED: 2010-02-22
PAPER REVISED: 2010-05-02
PAPER ACCEPTED: 2010-05-10
DOI REFERENCE: https://doi.org/10.2298/TSCI100222011N
CITATION EXPORT: view in browser or download as text file
THERMAL SCIENCE YEAR 2010, VOLUME 14, ISSUE Issue 4, PAGES [1089 - 110]
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Thermal and aerodynamic performances of the supersonic motion

© 2024 Society of Thermal Engineers of Serbia. Published by the Vinča Institute of Nuclear Sciences, National Institute of the Republic of Serbia, Belgrade, Serbia. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution-NonCommercial-NoDerivs 4.0 International licence