Aerodynamics and flight mechanics of MAV based on Coandă effect

Abstract

With the progress and development of Coandă Micro Air Vehicle (MAV) to date, various configurations have been proposed and developed. For the purpose of designing a Micro Air Vehicle (MAV), that could meet the desired mission and design requirements and can operate effectively in various environmental conditions, a workable theoretical analysis is to be developed. With such motivation, capitalizing on the basic fundamental principles, the aerodynamic forces acting on Coandă MAV configurations are revisited and analysed on the bases of the Fluid Dynamics and Flight Mechanics of a semi-spherical Coandă MAV configuration. The major objective of this paper is to analyse the forces and moments acting on the Coandă MAV as related to the geometry, flow, and motion parameters, using mathematical modelling. The mathematical model and derived performance measures in hover and translatory motion are shown to be capable in describing the physical phenomena of the flow field of the semi-spherical Coandă MAV. Results obtained are assessed and considered viable for preliminary design of such air vehicles and further elaborated development, including more flight dynamic manoeuvres.

Lift force for cylindrical and elliptical Coandă aircraft design

“…al. [13] and Schroijen and van Tooren [8] for two-dimensional cylindrical Coandă design model. From Figure 4, the result (solid line) have shown a good correlation and in agreement with the CFD data [3].…”

“…Basics of circulation control aerodynamics [3] Two versions of analytical formulation using control volume approach for the cylindrical Coandă aircraft have been presented by Schroijen and Van Tooren [8] and Ahmed et al [13]. In the first version [8], it has been concluded that the lift force is dependent on the jet velocity, outflow angle, dimensions of the jet slot, and introducing an efficiency parameter to capture the viscous effect.…”

“…The contribution of lift force is seems only derived from the jet-momentum. On the other hand, from the second version [13], it has clearly formulated the contributions of the pressure differential. While the effects due to the changes of the outflow angle and viscous flow effects are not included.…”

“…Derivation of the analytical formulation, given by Eqn. 10, is an extended version for cylindrical Coandă aircraft as presented earlier by Schroijen and van Tooren [8] and Ahmed et al [13].…”

“…Cylindrical/Elliptical Coandă configured aircraft model (adapted from Schroijen and van Tooren[8]) Pressure forces effect on two-dimensional cylindrical Coandă aircraft[13] …”