The main dimensions of the aircraft are the 5 m length from the nose to the tail,  a 2 m root chord, a 1 m root tip and the span of the wing is 7 m, it is also mounted 0.15 m below the x-axis with a 2º angle of attack. The difference in height between the wing and the horizontal tail is 1.38 m, having a tail span of around 4 m. The wing section fuselage of the aircraft has a diameter of 0.8 m, starting with a cone in the nose and finishing with a 0.3 m diameter truncated cone in the tail. These dimensions can be observed in Fig. 2, where it displays the 3D model of the aircraft. 

The MEA is a sophisticated aircraft remotely controlled from Mars, designed for effective and efficient flight. Its internal components, including flight control, navigation, propulsion, power, and communication systems, manage stability, attitude, and maneuverability. Sensors like GPS, barometer, camera, angle of attack, thermal, and IMU provide important data for navigation, mapping, and detection of anomalies. The Pixhawk computer is a reliable interface for processing data from various sensors. The electric propulsion system and power system with batteries supply thrust and electricity. The communication system enables real-time control and data transmission between the aircraft and Ground Control Station (GCS). Integration of sensors and cameras ensures safe and efficient operation throughout the Mars mission.

First, a motor and a propeller that have a combined weight of approximately 7 kg were chosen, which caused a large load on the front of the aircraft. Since this aircraft will be flown remotely, a navigational camera in the front of the plane was necessary for visual interpretation of the terrain and to aid the pilot. With a nose to tail length of 5 m, the nose landing gear was placed 0.5 m aft the nose and the main landing gear were added to be behind the center of gravity of the aircraft to avoid having a significant change in the location of the center of gravity. Lastly, the thermal camera and batteries were placed towards the back of the aircraft to compensate for the moments that were caused by the different components located on the front of the fuselage, See Fig. 3. With this internal layout, the location of the center of gravity was calculated to be 1.925 m aft the nose of the aircraft. A good estimation of the location of the center of pressure of the aircraft would be the quarter chord of the Mean Aerodynamic Chord, which leaves a static margin of 0.095. 

The NACA 0006 airfoil, a low-drag airfoil frequently used for unmanned aerial systems and small aircrafts, was chosen for MEA The low-drag qualities were crucial for maximizing the range and endurance of the aircraft. Many cambered airfoils were studied; however, they were directly disregarded due to the anomalies that arose when studying their graphs at low Reynolds Numbers. Moreover, when cambered airfoils were sized into wings, they failed to provide the general lift requirement for the aircraft to fly. 

In addition to its low-drag characteristics, the NACA 0006 airfoil is also relatively easy to manufacture and has been extensively tested in various wind tunnels and flight tests. These factors make it a reliable choice for the lift system, ensuring that the aircraft will be able to operate effectively in the challenging Martian environment. Overall, the NACA 0006 airfoil is an excellent choice for MEA, providing a reliable and efficient lift system that will enable this aircraft to explore and investigate the Red Planet.

Designing wings for a plane flying on Mars presents unique challenges due to the planet's thin atmosphere, this means that the wings must be larger to generate enough lift to keep the plane aloft. Due to the low air density, a low-wing design was opted for. One of its main advantages is its ability to provide better stability and handling, particularly during take off and landing. Having the wings closer to the ground means that the change in the static margin would be minimal while reducing drag. 

For the highest possible lift generation, the wing surface was maximized leading to a 7m wingspan and a mean aerodynamic chord (cW) of 1.56 m. Moreover, the wing was designed to have a root chord of 2m and a tip chord of 1m, creating a total wing area of 18.01 m2. The delta wing shape created a larger surface while smoothly connecting it to the fuselage creating better aerodynamics. 

A T-tail was chosen for the design to improve performance during cruise conditions, and decrease the effects of turbulence and other disturbances on the horizontal stabilizer as well as drag. On another note, the range of angles of attack that MEA can operate within is relatively small, therefore stalling is more probable. Therefore, the T-tail design opted for this phenomena and now the horizontal stabilizer is not present within the wake of the wing which makes the recovery of the aircraft from stalling easier.