Integrated Shap Optimization of RAE-M2129 Inlet for Aerodynamic Performance and Reduced Radar Cross Section

Unlu, T
Atasoy, M
Dincer, E
Eyi, Sinan
Low observability is a key quality of air breathing military aircrafts and the forward observability of such aircrafts are mostly determined by the open ended cavities formed by the air intakes. Geometrical shape of an S-duct intake has effect on both the radar signature indicated by radar cross section (RCS) and the aerodynamic performance indicated by pressure recovery (PR) and distortion coefficient (DC). In this study, shape optimization of RAE-M2129 S-duct inlet is done considering radar signature and key aerodynamic inlet performance parameters by constructing a multidisciplinary optimization cycle. The optimization is carried by a genetic algorithm with dedicated Python scripts generating variable surface shapes using a Bézier curve and running solver tools of computational fluid dynamics and electromagnetics with validated methods.
10th Ankara International Aerospace Conference, 2019


Experimental and numerical inestigation of an s-duct diffuser designed for a micro turbojet engine powered aircraft
Aslan, Samet; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2016)
S-duct diffusers are often used for aircraft propulsion systems that convey the intake air to the engine compressor. In this thesis, flow structure at separated entrance conditions in an S-duct diffuser that designed for a micro turbojet engine powered aircraft is investigated using experimental and numerical methods. Flow characteristics such as flow separation, secondary flows, and swirl are investigated to find out the source of distortions and pressure loss at aerodynamics interface plane. Experiments a...
Simulation of the Transient Response of a Helicopter Turboshaft Engine to Hot-Gas Ingestion
Uzol, Oğuz; Yavrucuk, İlkay (2008-06-09)
Hot-Gas Ingestion (HGI) to the engines can potentially occur when a rotorcraft or a VTOL/STOVL fixed-wing aircraft is operating in close proximity to the ground. Especially for helicopters, due to the rotor downwash hot exhaust gases get recirculated into the engine inlet. Similar conditions may also occur due to the ingestion of hot exhaust gases from rocket launchers or gun fire. In this study, we present the results of a simulation of the transient response of a helicopter turboshaft engine to HGI. Speci...
Design of an LPV Based Fractional Controller for the Vibration Suppression of a Smart Beam
Onat, Cem; Şahin, Melin; Yaman, Yavuz; Eswar, Prasad; Saılu, Nemana (2011-12-01)
One of the major problems encountered in the active vibration control of aircraft wings is the changing mass due to the in-flight fuel consumption. In this study, a Linear Parameter Varying (LPV) based fractional controller is designed for the suppression of the flexural vibrations of a smart beam. The designed controller is sensitive to the varying mass properties. The smart beam studied was a cantilever aluminium beam with eight surface bonded Lead-Zirconate-Titanate (PZT) patches. The smart beam was exci...
An enhanced analytical model for residual stress prediction in machining
Lazoglu, I.; Ulutan, D.; Alaca, B. E.; Engin, S.; Kaftanoglu, B. (2008-01-01)
The predictions of residual stresses are most critical on the machined aerospace components for the safety of the aircraft. In this paper, an enhanced analytic elasto-plastic model is presented using the superposition of thermal and mechanical stresses on the workpiece, followed by a relaxation procedure. Theoretical residual stress predictions are verified experimentally with X-ray diffraction measurements on the high strength engineering material of Waspaloy that is used critical parts such as in aircraft...
High-alpha flight maneuverability enhancement of a fighter aircraft using thrust-vectoring control
Atesoglu, Oezguer; Oezgoeren, M. Kemal (American Institute of Aeronautics and Astronautics (AIAA), 2007-09-01)
This study focuses on high-alpha flight maneuverability enhancement of a fighter-bomber aircraft for air combat superiority using thrust-vectoring control. Two basic air superiority maneuvers are studied as test cases, which are the Cobra maneuver with longitudinal motion and the Herbst maneuver with both longitudinal and lateral motions. The necessary mathematical models are built to describe the nonlinear 6-degree-of-freedom flight dynamics, the nonlinear aerodynamics, the engine, and the thrust-vectoring...
Citation Formats
T. Unlu, M. Atasoy, E. Dincer, and S. Eyi, “Integrated Shap Optimization of RAE-M2129 Inlet for Aerodynamic Performance and Reduced Radar Cross Section,” Ankara, Türkiye, 2019, vol. 10, Accessed: 00, 2021. [Online]. Available: