inproceedings by Benoit Marinus
La construction durable en utilisant des techniques passives: concept et simulation
Truncated method for propeller noise prediction up to low supersonic helical tip {M}ach numbers
Modified actuator disk with non-uniform loading and blade wake velocity deficit
Influence of parameterization and optimization method on the optimum airfoil
Current status of propeller blade multidisciplinary optimization
Aeroacoustic and aerodynamic optimization of aircraft propeller blades
Toward multidisciplinary optimization of propeller blades
Multidisciplinary Optimization of Propeller Blades: focus on the aeroelastic results
Multidisciplinary Optimization of Propeller Blades: focus on the aeroacoustic results
Aerodynamic study of a 'humpy' propeller
Influence of {OEI}-conditions for a Down Between Engines configuration of a propeller equipped aircraft
Comparative Study of the Effects of Sweep and Humps on High-Speed Propeller Blades
Fast Prediction Model for Tonal Noise from Propellers or Rotors
Effect of Rotation on the 3D Boundary Layer around a Propeller Blade
Characterization of the broadband noise of mini RPA propeller blades
Trailing Edge Noise of Innovative Mini-RPA Propeller Blade Geometry
Broadband Noise from Serrated UAS Propellers: Validation of a Lattice Boltzmann Approach
With the increased use on Unmanned Aerial Systems equipped with propellers and rotors, serrated e... more With the increased use on Unmanned Aerial Systems equipped with propellers and rotors, serrated edges
are considered to reduce broadband noise emissions without affecting the aerodynamic performance. In this
context, a full sensitivity study is performed to assess the independence of the solution to the space (voxel
resolution) and time discretization (time step, sampling rate and number of revolutions). This way, the
computational tools are validated for the prediction of both the aerodynamic and aeroacoustic performance.
The results show there is enough confidence in such models for them to be used to optimize serrated propeller
geometries and achieve a reduction of the noise emissions by 3~10dB in the 1000Hz to 10.000Hz range.
Influence of Crossing the Transonic Domain for Precision Ammunition
Analytical Investigation of Turbulence Interaction Noise of Mini-{RPA} Serrated Blades
Aerodynamical {CFD} Study of a Non-lethal 12-gauge Fin-stabilized Projectile
Nowadays, the trajectory model for a subsonic fin-stabilized projectile at low angle of attack is... more Nowadays, the trajectory model for a subsonic fin-stabilized projectile at low angle of attack is typically a point-mass model (PMM), taking only gravity and a constant zero-yaw drag into account. This choice can be qualitatively justified for non-lethal projectiles given the short ranges. The disadvantage of this approach is the lack of prediction on the precision and the attitude of the projectile when hitting the target, because of a possible instability in flight. However, the use of non-lethal projectiles requires that the impact conditions are met, otherwise more serious injuries may occur. Therefore, the consideration of other forces and moments acting on the projectile in flight is mandatory to predict static and dynamic stability, already in the body shape design as well as in the controller design process in the field of non-lethal ammunitions. Starting from a geometry in caliber 12-gauge, static coefficients (drag, lift and pitch) for different angles of attack using steady RANS-simulations with a low-order turbulence model were found. Different trajectories were then analysed using those coefficients and the difference between the PMM and a 3-DOF accounting for drag, lift and pitch in function of the angle of attack is indeed negligible in height and in range as long as the launch conditions are completely undisturbed. The slightest destabilization makes the PMM completely inappropriate. Knowledge of the pitch damping coefficient then becomes a necessity to optimize stabilization following minor disturbances.
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inproceedings by Benoit Marinus