THERMAL SCIENCE

International Scientific Journal

Authors of this Paper

External Links

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
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 4, PAGES [1089 - 110]
REFERENCES
  1. Janković, S., Aerodynamics of the projectiles (in Serbian), TŠC KoV JNA, SFRJ, 1972
  2. Jankovic S.: Aerodynamics of the projectiles (in Serbian), Faculty of Mechanical Enigineering, Belgrade, Belgrade, SFRJ, 1979
  3. Mason, L., et al, Aerodynamic Design Manual for Tactical Weapons, Manual, Naval Surface Weapons Center, Dahlgren, Vir., USA, 1973
  4. Quinn, R. D., Gong, L., Real-time Aerodynamic Heating and Surface Temperature Calculations for Hypersonic Flight Simulation, Report NASA Technical Memorandum 4222, Ames Research center, Dryden Flight Research Facility, Edwards, Ca., USA, 1990
  5. Quinn, R. D., Gong, L., A Method for Calculating Transient Surface Temperatures and Surface Heating Rates for High-Speed Aircraft, Report NASA /TP-2000-209034, Dryden Flight Research Center, Edwards, Ca., USA, 2000
  6. Moore, J. A., Natonal Advisory Committee for Aeronautics Research Memorandum, Report NACA RM L57G10a, Langley Aeronautical Laboratory, Langley Field, Wa., USA, 1957
  7. Martin, J. C., Jeffreys, I., National Advisory Committee for Aeronautics technical note 2643, Report NACA TN 2643, Langley Aeronautical Laboratory, Langley Field, Wa., USA, 1952.
  8. Ninković, D., Mathe¬matical model of the wing in supersonic flow (in serbian), M.Sc. thesis, Faculty of Mechanical Engineering, Belgrade, Serbia, 2004
  9. Ninković D., Modifications of the equations for distribution of circulation for tapered, sweptback wings with streamwise tips in the supesrsonic flow presented in NACA TN 2643 paper, Scientifical technical review (NTP), 1 (2005), 55, pp 70-79
  10. Ninković D., G.R.O.M. Software for Determination of the Aerodynamic Derivatives Values for Isolated Wing in Supersonic Flow, Scientifical technical review (NTP), 2 (2004), 54, pp 66-75

© 2019 Society of Thermal Engineers of Serbia. Published by the Vinča Institute of Nuclear Sciences, 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