Sökning: "transonic flow"
Visar resultat 11 - 15 av 36 avhandlingar innehållade orden transonic flow.
11. Large Eddy Simulations of Separated Compressible Flows around Wing Sections
Sammanfattning : This thesis concerns numerical calculations of compressible separated flows, with and without shocks, around wing sections using Large Eddy Simulations (LES). The considered geometries are the NACA 0012 wing section and the ONERA AT15A wing section. LÄS MER
12. Modal Analysis of Supersonic Flow Separation in Nozzles
Sammanfattning : Operating a convergent-divergent nozzle under overexpanded conditions can lead to supersonic flow separation in the divergent section of the nozzle. In this case, an attached oblique shock wave forms at the separation base. LÄS MER
13. Numerical Investigation of Aerodynamic Blade Excitation Mechanisms in Transonic Turbine Stages
Sammanfattning : With the present drive in turbomachine engine developmenttowards thinner and lighter bladings, closer spaced blade rowsand higher aerodynamic loads per blade row and blade, advanceddesign criteria and accurate prediction methods for vibrationalproblems such as forced response become increasingly importantin order to be able to address and avoid fatigue failures ofthe machine early in the design process. The present worksupports both the search for applicable design criteria and thedevelopment of advanced prediction methods for forced responsein transonic turbine stages. LÄS MER
14. Hot wire and PIV studies of transonic turbulent wall-bounded flows
Sammanfattning : The compressible turbulent boundary layer developing over atwo-dimensional bump which leads to a supersonic pocket with aterminating shock wave has been studied. The measurements havebeen made with hot-wire anemometry and Particle ImageVelocimetry (PIV). LÄS MER
15. A Linearized Euler Method for Unsteady Flow in Axial-Flow Turbomachines
Sammanfattning : A linear Euler method for analysing unsteady inviscid compressible quasi three- dimensional flows in oscillating cascades is developed. It is applicable to both blade flutter and forced response problems. LÄS MER