NUMERICAL AND EXPERIMENTAL ANALYSIS OF FLAPPING MOTION IN HOVER. APPLICATION TO MICRO AIR VEHICLES.


Kurtuluş D. F.

Diğer, ss.1-262, 2005

  • Basım Tarihi: 2005
  • Sayfa Sayıları: ss.1-262

Özet

The aerodynamics phenomena of flapping motion in hover are considered in view of the future Micro Air Vehicle applications. The aim of this work is to characterize the vortex dynamics generated by the wing in motion using direct numerical simulation and experimental analysis then to propose a simplified analytical model for prediction of the forces in order to optimize the parameters of the motion leading to maximum force. A great number of cases are investigated corresponding to different angles of attack, location of start of change of incidence, location of start of change of velocity, axis of rotation, and Re number. The airfoil used is symmetrical. The flow is assumed to be incompressible and laminar with the Reynolds numbers between 500 and 2000. The experimental results obtained by the laser sheet visualization and the Particle Image Velocimetry (PIV) techniques are used in parallel with the direct numerical simulation results for the phenomenological analysis of the flow. The model developed for the aerodynamic forces is an indicial iv method based on the use of the Duhamel Integral and the results obtained by this model are compared with the ones of the numerical simulations.