Investigation on Effect of 20% Shrinkage and 20% Shrinkage-Offset Canard Configurations on Aerodynamic Characteristics of Onera M6 wing using Computational Fluid Dynamics

Abstract

The main objective of the analysis is to study the detailed aerodynamics & the characteristics of the lift & drag of the aircraft with the canard wing & the co-efficient of pressure & flow separation patterns over the wings at different spans and angles of attacks. Here the Onera-M6 wing is modelled for the transonic flow conditions in 3D with the adiabatic flow conditions. In the first case only the Onera-M6 wing is analyzed to know the performance. In the second case the canard is considered along with the Onera-M6 main wing and the modelling is done with the same set of conditions as 3D- transonic flows. In the present study two canard positions are considered, one under the same axis of the main wing (20% shrinkage), and another above the axis line of the main wing (20% shrinkage-offset). In the first design i.e., canard of 20% shrinkage with same axis, the design is performing well than clean wing & 20% shrinkage-offset canard at the lower angle of attacks. In the second design i.e., canard with 20% shrinkage-offset with the axis of the main wing is analyzed at different angles of attacks, the design is performing better than clean wing & 20% shrinkage with the same axis at higher angles of attacks.