COMPUTATIONAL FLUID DYNAMIC SIMULATION FOR ROTOR-BODY-INTERACTION (ROBIN) MODEL AND COMPARISON WITH EXPERIMENT

YUNUS EMRE SUNAY

ROKETSAN Missile Industries Inc., P.K.:30, 06780 Elmadağ-Ankara-Türkiye, esunay@roketsan.com.tr

ALİ AKGÜL

ROKETSAN Missile Industries Inc., P.K.:30, 06780 Elmadağ-Ankara-Türkiye, aakgul@roketsan.com.tr

İSKENDER KAYABAŞI

ROKETSAN Missile Industries Inc., P.K.:30, 06780 Elmadağ-Ankara-Türkiye, ikayabasi@roketsan.com.tr

Abstract: The carriage and release of missile from helicopter are primary importance to missile-integration analysis in Missile Development Projects. The accurate prediction of the trajectory of a missile released from a helicopter is critical in assessing whether the store can be released safely as well as if it will accurately reach its target. Especially in the low dynamic pressure region, vertical velocity (downwash) caused from rotor on the body is important issue in terms of missile-separation. In this study, Computational Fluid Dynamics (CFD) analyses are done to investigate the effect of downwash due to helicopter rotor. In order to make flow field simulation due to rotor-helicopter interaction, three main models: Moving Reference Frame (MRF), Sliding Mesh Model (SMM) and Virtual Blade Model (VBM) are used to analyze downwash effect of the helicopter. In this study, calculation of the downwash effect with CFD are validated and verified by comparison of experimental study. In this study, various CFD simulations are performed using Rotor Body Interaction (ROBIN) test case. ROBIN is a generic helicopter model and most commonly used test case to validate prediction tools for the helicopter flow field analysis