In this thesis the validation of a computational fluid dynamics (CFD) code against published experimental data and alternative CFD results is explored. Six case studies are presented with flow speeds ranging from mid supersonic to hypersonic. The studies include complex compressible flow phenomena such as the interaction of shockwaves with boundary layers, vortices and other shockwaves. Two of the six validation cases also consider complex thermodynamic behaviour such as vibrational and chemical nonequilibrium. The problems chosen are limited in scope to flows which are planar or axisymmetric and remain laminar throughout the region of flow studied. This allows the studies to focus on simulating the fundamental behaviour of the flow without the added complication of turbulence or the need for large scale computing facilities. The problems which arose during the validation studies and a background to why they occurred and, wherever possible, strategies to avoid their occurrence are discussed. General modelling strategies in compressible CFD are also discussed. In this thesis the software suite CFD-FASTRAN is used to construct and analyse the CFD models. The material presented in this thesis is however general such that users of similar packages should find the thesis beneficial.

In this thesis the validation of a computational fluid dynamics (CFD) code against published experimental data and alternative CFD results is explored. Six case studies are presented with flow speeds ranging from mid supersonic to hypersonic. The studies include complex compressible flow phenomena such as the interaction of shockwaves with boundary layers, vortices and other shockwaves. Two of the six validation cases also consider complex thermodynamic behaviour such as vibrational and chemical nonequilibrium. The problems chosen are limited in scope to flows which are planar or axisymmetric and remain laminar throughout the region of flow studied. This allows the studies to focus on simulating the fundamental behaviour of the flow without the added complication of turbulence or the need for large scale computing facilities. The problems which arose during the validation studies and a background to why they occurred and, wherever possible, strategies to avoid their occurrence are discussed. General modelling strategies in compressible CFD are also discussed. In this thesis the software suite CFD-FASTRAN is used to construct and analyse the CFD models. The material presented in this thesis is however general such that users of similar packages should find the thesis beneficial.

In this thesis the validation of a computational fluid dynamics (CFD) code against published experimental data and alternative CFD results is explored. Six case studies are presented with flow speeds ranging from mid supersonic to hypersonic. The studies include complex compressible flow phenomena such as the interaction of shockwaves with boundary layers, vortices and other shockwaves. Two of the six validation cases also consider complex thermodynamic behaviour such as vibrational and chemical nonequilibrium. The problems chosen are limited in scope to flows which are planar or axisymmetric and remain laminar throughout the region of flow studied. This allows the studies to focus on simulating the fundamental behaviour of the flow without the added complication of turbulence or the need for large scale computing facilities. The problems which arose during the validation studies and a background to why they occurred and, wherever possible, strategies to avoid their occurrence are discussed. General modelling strategies in compressible CFD are also discussed. In this thesis the software suite CFD-FASTRAN is used to construct and analyse the CFD models. The material presented in this thesis is however general such that users of similar packages should find the thesis beneficial.

In this thesis the validation of a computational fluid dynamics (CFD) code against published experimental data and alternative CFD results is explored. Six case studies are presented with flow speeds ranging from mid supersonic to hypersonic. The studies include complex compressible flow phenomena such as the interaction of shockwaves with boundary layers, vortices and other shockwaves. Two of the six validation cases also consider complex thermodynamic behaviour such as vibrational and chemical nonequilibrium. The problems chosen are limited in scope to flows which are planar or axisymmetric and remain laminar throughout the region of flow studied. This allows the studies to focus on simulating the fundamental behaviour of the flow without the added complication of turbulence or the need for large scale computing facilities. The problems which arose during the validation studies and a background to why they occurred and, wherever possible, strategies to avoid their occurrence are discussed. General modelling strategies in compressible CFD are also discussed. In this thesis the software suite CFD-FASTRAN is used to construct and analyse the CFD models. The material presented in this thesis is however general such that users of similar packages should find the thesis beneficial.

In this thesis the validation of a computational fluid dynamics (CFD) code against published experimental data and alternative CFD results is explored. Six case studies are presented with flow speeds ranging from mid supersonic to hypersonic. The studies include complex compressible flow phenomena such as the interaction of shockwaves with boundary layers, vortices and other shockwaves. Two of the six validation cases also consider complex thermodynamic behaviour such as vibrational and chemical nonequilibrium. The problems chosen are limited in scope to flows which are planar or axisymmetric and remain laminar throughout the region of flow studied. This allows the studies to focus on simulating the fundamental behaviour of the flow without the added complication of turbulence or the need for large scale computing facilities. The problems which arose during the validation studies and a background to why they occurred and, wherever possible, strategies to avoid their occurrence are discussed. General modelling strategies in compressible CFD are also discussed. In this thesis the software suite CFD-FASTRAN is used to construct and analyse the CFD models. The material presented in this thesis is however general such that users of similar packages should find the thesis beneficial.

In this thesis the validation of a computational fluid dynamics (CFD) code against published experimental data and alternative CFD results is explored. Six case studies are presented with flow speeds ranging from mid supersonic to hypersonic. The studies include complex compressible flow phenomena such as the interaction of shockwaves with boundary layers, vortices and other shockwaves. Two of the six validation cases also consider complex thermodynamic behaviour such as vibrational and chemical nonequilibrium. The problems chosen are limited in scope to flows which are planar or axisymmetric and remain laminar throughout the region of flow studied. This allows the studies to focus on simulating the fundamental behaviour of the flow without the added complication of turbulence or the need for large scale computing facilities. The problems which arose during the validation studies and a background to why they occurred and, wherever possible, strategies to avoid their occurrence are discussed. General modelling strategies in compressible CFD are also discussed. In this thesis the software suite CFD-FASTRAN is used to construct and analyse the CFD models. The material presented in this thesis is however general such that users of similar packages should find the thesis beneficial.

In this thesis, store separation from two different configurations are solved using computational methods. Two different commercially available CFD codes / CFD-FASTRAN, an implicit Euler solver, and an unsteady panel method solver USAERO, coupled with integral boundary layer solution procedure are used for the present computations. The computational trajectory results are validated against the available experimental data of a generic wing-pylon-store configuration at Mach 0.95. Major trends of the separation are captured. Same configuration is used for the comparison of unsteady panel method with Euler solution at Mach 0.3 and 0.6. Major trends are similar to each other while some differences in lateral and longitudinal displacements are observed. Trajectories of a fueltank separated from an F-16 fighter aircraft wing and full aircraft configurations are found at Mach 0.3 using only the unsteady panel code. The results indicate that the effect of fuselage is to decrease the drag and to increase the side forces acting on the separating fueltank from the aircraft. It is also observed that the yawing and rolling directions of the separating fueltank are reversed when it is separated from the full aircraft configuration when compared to the separation from the wing alone configuration.