The preliminary analysis of laminate composite was conducted to analyse the optimal number of layers for aircraft radome application. In this work, the ESAComp software was used for preliminary analysis to predict the displacement during the flight operation. The ESAComp is a finite element software used for preliminary and conceptual design for composite layers. Flax fibre, glass fibre and epoxy resin were applied as the hybrid composite laminate design. The laminate construction consists of flax as the center laminate and sandwiched between glass fibre. Both fibres have the same weave pattern which is twill 2/2 and 200 gsm. The material properties for each materials were obtained from technical data sheet and used as input value for ESAComp. This software was used to analyse a single ply engineering constant by conducting fibre/matrix micromechanics analysis. The value of engineering constant of single ply for each material is then used for laminate analysis. It has range from 4,6 and 8 layers with 20%, 30% and 40% of fibre content on a flat panel with the size of 300 mm x 300 mm. The panel were fixed on each edges and under aerodynamic pressure load plus safety factor of two. Based on the result of analysis, minimum layer required is at least 6 layers if acceptance displacement is 0.1 mm. Therefore, experimental works on 6 layers hybrid laminate will be carried out to determine other requirement for aircraft radome application.