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DEUTSCH
ENGLISH
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Investigations in Aerodynamics
Purpose
- Conception and evaluation of:
o aerodynamic architectures of flying
vehicles (gun-launched vehicles, …),
o control devices of flying vehicles
(canards, fins, jets, plasmas, …),
- Studies of aerodynamic fundamental phenomena encountered in various flight conditions (boundary layer transition, separation, reattachment, Magnus effect, …).
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Facilities
- High enthalpy shock-tubes and blow-down wind tunnel (Mach number
ranging from 1.4 to 10) equipped with
up-to-date local (LDA, pressure,
heat-flux) measurement equipment
- and global (PIV, DGV, DPV, PSP, BOS, temperature, high-speed visualization, force-balance, FFM ...) measuring systems
- Subsonic wind tunnel and shock tube equipped with the same measurement techniques
- 3D Navier-Stokes Computational Fluid Dynamics Code
(RANS, URANS) running on a cluster. |
Skills
- Carrying out particular techniques for specifi c investigations on projectile aerodynamics:
o free-flight of models in a shock
tube for drag, lift and pitching
moment evaluation,
o test rig for free-spinning projectiles,
roll-, pitch- and yaw-angles
determination in wind tunnels,
- Measurement techniques in shock tubes and wind tunnels
- Analysis of numerical results in order to better understand the physics of the complex 3D fl ow fi eld around fl ying
vehicles. |
Results
- Evaluation, conception and optimization of aerodynamic architectures of various flying vehicles
- Studies of various control devices for projectiles and missiles (lateral jet, canards, plasma discharge, ...)
- Heating of supersonic and hypersonic projectiles and missiles
- Simulation of the behaviour of the jet plume formed during the starting phase of a vertical launched missile.
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Free-flight of a projectile in a shock tube (FFM)
Visualization Numerical simulation
Vertical launcher of a missile |
Wind tunnel rig for the study of roll-damping and pitch-damping effects of free-spinning models at supersonic speed
Visualization Numerical simulation
Guidance by plasma discharge
Guidance by Lateral Jet at Supersonic Speed: Pressure Measurement (PSP) |
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