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Supersonic transport (SST) technology has widely been investigated. Flow characteristics become complicated in supersonic conditions, and aerodynamic shape optimization studies are required for the design process of supersonic vehicles. An optimized aircraft is very efficient in terms of fuel consumption and pressure losses. This study focuses on the aerodynamic design and shape optimization of a supersonic business jet. For this purpose, a design algorithm (BF-I) is developed with the help of historical trends of supersonic aircrafts, commercial aircrafts and experimental correlations. After obtaining the baseline geometry, a gradient-based optimization is employed to get optimum results for the design. The developed numerical methodology is tested for both 2D and 3D geometries. CFD analysis are performed by using SU2 (Stanford University Unstructured) solver that has high performance for compressible flows. Euler equations are used for the analyses. © 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

Supersonic transport (SST) technology has widely been investigated. Flow characteristics become complicated in supersonic conditions, and aerodynamic shape optimization studies are required for the design process of supersonic vehicles. An optimized aircraft is very efficient in terms of fuel consumption and pressure losses. This study focuses on the aerodynamic design and shape optimization of a supersonic business jet. For this purpose, a design algorithm (BF-I) is developed with the help of historical trends of supersonic aircrafts, commercial aircrafts and experimental correlations. After obtaining the baseline geometry, a gradient-based optimization is employed to get optimum results for the design. The developed numerical methodology is tested for both 2D and 3D geometries. CFD analysis are performed by using SU2 (Stanford University Unstructured) solver that has high performance for compressible flows. Euler equations are used for the analyses. © 2015, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

A Computational Fluid Dynamics (CFD) study is conducted to investigate the unsteady, turbulent supersonic cavity flow characteristics and to control the severe effects of the flow field. Simulations of Mach 1.5 supersonic cavity flow with a length to depth ratio of 5.07 are performed using commercial ANSYS Fluent solver. Unsteady density-based Reynolds Averaged Navier-Stokes equations are modeled with standard k-? turbulence model. Both baseline simulations with no control and simulations with passive and active control methods are examined. Implemented passive control methods are trailing edge wall inclination, cavity entrance cover plate, and wall spoilers. Microjet blowing is applied as an active control method. For further investigation of the flow field and to distinguish the dominant features of the controlled and uncontrolled cases, Proper Orthogonal Decomposition (POD) is applied to velocity data obtained from the inside of the cavity. CFD and POD studies represent promising results for flow control in terms of suppressing undesired effects of cavity flow oscillations. © 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

A Computational Fluid Dynamics (CFD) study is conducted to investigate the unsteady, turbulent supersonic cavity flow characteristics and to control the severe effects of the flow field. Simulations of Mach 1.5 supersonic cavity flow with a length to depth ratio of 5.07 are performed using commercial ANSYS Fluent solver. Unsteady density-based Reynolds Averaged Navier-Stokes equations are modeled with standard k-? turbulence model. Both baseline simulations with no control and simulations with passive and active control methods are examined. Implemented passive control methods are trailing edge wall inclination, cavity entrance cover plate, and wall spoilers. Microjet blowing is applied as an active control method. For further investigation of the flow field and to distinguish the dominant features of the controlled and uncontrolled cases, Proper Orthogonal Decomposition (POD) is applied to velocity data obtained from the inside of the cavity. CFD and POD studies represent promising results for flow control in terms of suppressing undesired effects of cavity flow oscillations. © 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.