Three dimensional flowfields about a winged space vehicle at supersonic speed were numerically simulated using Navier-Stokes equations. The present model of the vehicle is under study at the National Aerospace Laboratory as a candidate Japanese future aerospace vehicle. Here, interest is concentrated on the understanding of the effect of the tail wing on the shape of the vehicle. So, two different simulations were conducted; one is for the flowfields about a whole configuration model (WBT Model) and the other is about a wing-body combination model (WB Model). The vortical flow phenomena due to high angle of attack are so complicated that a more careful consideration is necessary. The numerical results show the difference clearly between those two flowfields. The aerodynamic forces and coefficients computed from the simulation results are in good agreement with experimental data.
Aerodynamic Simulation of Flows About a Space-Plane 3
1989
6 pages
Report
Keine Angabe
Englisch
Spacecraft Trajectories & Flight Mechanics , Aerodynamics , Aircraft , Fluid Mechanics , Aerospace planes , Body-wing configurations , Computational fluid dynamics , Flow distribution , Supersonic speed , Three dimensional flow , Wings , Computerized simulation , Aerodynamic coefficients , Aerodynamic forces , Angle of attack , Japan , Navier-stokes equation , Shapes , Foreign technology
AERODYNAMIC SIMULATION OF FLOWS IN A HIGHLY LOADED TURBINE
British Library Conference Proceedings | 2011
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