24th Congress of International Council of the Aeronautical Sciences, 29 August-3, September 2004, Yokohama, Japan
Paper ICAS 2004-2.7.R.1

NUMERICAL STUDY OF SHOCK GENERATION AT THE AFTER-BODY OF SLENDER BODY OF REVOLUTION USING NAVIER-STOKES EQUATION

E. Priyono, L. R. Zuhal, H. Djojodihardjo
Department of Aeronautics and Astronautics, Institute of Technology Bandung, Indonesia

Keywords: transonic flow, aerodynamics, axi-symmetric flow, shock-generation

The present work looks into the mechanism of drag due to shockwaves generated at the aft-part of a slender body, in another effort to optimize the total drag from physical consideration. In this regard, numerical approach is carried out following the well established computational fluid dynamic method in solving the Navier-Stokes equation around an axi-symmetric body in transonic flow.

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