Design and Analysis of Aluminium Matrix Composite Aircraft …
55
3 Design and Analysis of Wing
NACA0012 airfoil has been chosen for designing and analysing the wing of the
aircraft. Basic Calculations has been done for knowing different parameters of the
wing. Literature survey has been done and many values have been taken from that.
Table 1 shows some of the parameters taken from the literature survey.
From all the above values, wing has been designed in CATIA. Figure 1 shows the
basic design of NACA0012 airfoil and Fig. 2 shows designed CATIA modal of the
wing of the aircraft.
After designing the wing, it has been analysed in ANSYS. Finite element analysis
and flow analysis has been performed on the wing. Density of the material has been
given as 2.93. Toughness was found to be 75 J/m, Hardness was found to be 82 HRA
and Ultimate strength was 725 Mpa. Figure 3 shows the mesh modal of the wing that
has been done in ANSYS.
Fine meshing has been done in the wing. 1,334,493 nodes and 25,536 elements
have been created over the whole model. Refinement has been done over whole wing.
Table 1 Parameters of wing
S. No.
Parameters
Value
1
Wing area (m 2 )
41.94
2
Aspect ratio
7.3
3
Wing span (m)
17.73
Fig. 1 Design of NACA0012
55
3 Design and Analysis of Wing
NACA0012 airfoil has been chosen for designing and analysing the wing of the
aircraft. Basic Calculations has been done for knowing different parameters of the
wing. Literature survey has been done and many values have been taken from that.
Table 1 shows some of the parameters taken from the literature survey.
From all the above values, wing has been designed in CATIA. Figure 1 shows the
basic design of NACA0012 airfoil and Fig. 2 shows designed CATIA modal of the
wing of the aircraft.
After designing the wing, it has been analysed in ANSYS. Finite element analysis
and flow analysis has been performed on the wing. Density of the material has been
given as 2.93. Toughness was found to be 75 J/m, Hardness was found to be 82 HRA
and Ultimate strength was 725 Mpa. Figure 3 shows the mesh modal of the wing that
has been done in ANSYS.
Fine meshing has been done in the wing. 1,334,493 nodes and 25,536 elements
have been created over the whole model. Refinement has been done over whole wing.
Table 1 Parameters of wing
S. No.
Parameters
Value
1
Wing area (m 2 )
41.94
2
Aspect ratio
7.3
3
Wing span (m)
17.73
Fig. 1 Design of NACA0012