REPUBLIC OF SERBIA

MINISTRY OF DEFENCE

www.mod.gov.rs

MINISTRY OF DEFENCE

Material Resources Sector

Defensive Technologies Department

Military Technical Institute

www.vti.mod.gov.rs

COMPUTATIONAL AND EXPERIMENTAL DETERMINATION OF SUBSONIC PRESSURE DISTRIBUTION FOR MISSILE CALIBRATION MODEL

SLOBODAN STUPAR

University of Belgrade, Faculty of Mechanical Engineering, Belgrade, Serbia, sstupar@mas.bg.ac.rs

JOVAN ISAKOVIĆ

Military Technical Institute, Belgrade, Belgrade, Serbia, jovanisakovic@gmail.com

DRAGAN KOMAROV

University of Belgrade, Faculty of Mechanical Engineering, Belgrade, Serbia,  dkomarov@mas.bg.ac.rs

DIJANA DAMLJANOVIĆ

Military Technical Institute, Belgrade,Belgrade, Serbia,  didamlj@gmail.com

ALEKSANDAR SIMONOVIĆ

University of Belgrade, Faculty of Mechanical Engineering, Belgrade, Serbia, asimonovic@mas.bg.ac.rs

Abstract: Flow around the missile calibration model was investigated. Computationally determined pressure distribution and base pressure were compared to the results obtained in T-38 trisonic blowdown wind tunnel of the Military Technical Institute of Serbia. The computations were done for Mach 0.6. The model configuration consisted of cylindrical body with spherically blunted tangent ogive nose, increase of diameter at the base, and four fins in cruciform configuration. Brief overview of test installation and experiment methodology was given. Finite volume solver was used to solve unsteady governing equations for the compressible flow. Results for different turbulence models were compared with experiment. In addition, qualitative analysis of the computational data of the base flow was done. The recirculation regions with lower pressure are identified. More complex flow simulations are needed in order to accurately capture flow structures in the base region. Obtained results can be useful for further numerical and experimental investigations of base flow phenomena.

Key words: ogive cylinder, wind tunnel, CFD, pressure distribution, base pressure