Domain specific Tasks

TASK 1: History of Aviation

Objective:
To understand the history of aviation and the parts of planes and their technical names and the thought process behind the advancement in the aviation sector.
Outcomes&Learning:

History of Aviation

The history of aviation started in China with kite. It was one of the wonderful journey from kite to jets, cargopalnes, drones and many more. The following picture can explain the journey of aviation sector
Nowadays Aviation sector is growing field and it is an important mode of transport and in defense sector.
Here is the image of an jet flying in the sky with joy

Parts of Plane

Plane is a complicated and technical thing that involves many number of things to operate smoothly.
Here are some basic parts of planes

TASK 2: Simulation Flying

Objective:
To Gain hands-on experience with fundamental drone maneuvers and understand the importance of maintaining line of sight while operating a UAV. Use a simulator to observe drone speed, range, and the rotation of axes, and tackle various flying challenges.
Outcomes&Learnings:
I used RDS(Real Drone Simulator) to simulate the working of drone. The speed of the drone in the simulator is high it is very difficult to control the drone. Somehow i learnt to control in some manner.
Here are some glimpses while learning and playing:
RDS gives the platform to customize the drone I played the race and common fly Many times it crashed and as same many times i won the race

TASK 3: Design an Airfoil in fusion 360

Objective:
Design an airfoil with NACA 4412 coordinates in Fusion 360. Use the DAT to spline converter or canvas tool to sketch the airfoil. Understand terms such as angle of attack, camber line, chord line, and leading edge. Design two versions: one using a wood environment and another using composites. The wing should generate at least 5 newtons of lift at a wind speed of 25 m/s.

Outcomes&Learning:
I have learnt about airfoils and it's shapes and about NACA 4412. \

Labelled Diagram of airfoil:

NACA 4412 Characteristics:

Camber: The NACA 4412 has a maximum camber of 4% of the chord.
Camber Location: The maximum camber is located at 40% of the chord length from the leading edge.
Thickness: The airfoil has a maximum thickness of 12% of the chord.