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

development OF ıntake desıgn methodology for ramjet mıssıle

Erkut BAŞKUT

ROKETSAN, Ankara-Türkiye,  ebaskut@ roketsan.com.tr

ALİ AKGÜL

ROKETSAN, Ankara-Türkiye, aakgul@ roketsan.com.tr

Abstract: In this study, a conceptual intake design methodology is developed for supersonic cruise missiles with Ramjet engine in order to predict performance parameters of the intake such as pressure recovery, total capture area ratio, flow distortion and performance of the intakes for various operating conditions.  Optimum design shape and size of the intake and performance estimation of the intake for the various operating conditions is calculated using AEROINLET design code which is developed in ROKETSAN. Obtained results of analytical methods are compared with the results of inviscid CFD analyses in terms of intake shock patterns, pressure recovery and mass flow ratio.

Key words: Supersonic Inlet, Intake Design, Ramjet, CFD, AEROINLET