ersinaytac

I started working on a flying wing and a quadrotor projects theoretically. After reading a while I realize that i have no idea about the aeronautical terminology.

Here is the list of the terms I came across , i'll add more if i need to.

Fuselage is the the aircrafts main body section.



Airfoil is the shape of the wing.
Chord is the imaginary straight line joining the trailing edge and the center of curvature of the leading edge of the cross-section of an airfoil.
Tip Chord is the far end of the chord.
Root Chord is where the chord is attached to the fuselage.
Chord length is the distance between the trailing edge and the point on the leading edge where the chord intersects the leading edge.
Leading edge is the part of the wing that first contacts the air.
Trailing edge is the rear edge of the wing, where the airflow separated by the leading edge rejoins after passing over and under the top and bottom surfaces of the wing.



MAC ( Mean Aerodynamic Chord) is the chord of a rectangular wing, which has the same area, aerodynamic force and position of the center of pressure at a given angle of attack as the given wing has.



How to find MAC on a DeltaWing.



Lets say
Length of Root Chord = B
Length of Tip Chord = A

We add length of Root Chord to the up and bottom of the Tip of the Chord also do the same ting for the tip of chord.
As shown in the drawing I numbered from 1 to 4 each tip. Connect the 1&4 and 2&3, get a point on the wing. Draw a parallel line to tip/root of the chord, you'll have the MAC line.

Wing Area





Total Wing Area is the total area of both wings.

Calculating the wing area for a Tapered & Swept Wing




Average Chord = (Length of the Root Chord + Length of the Tip Chord) / 2
Wing Area = Wing Span * Average Chord

Wing Span is the distance from one wingtip to other wingtip.





Swept Wing is a wing platform with a wing root to wingtip direction angled beyond the spanwise axis, generally used to delay the drag rise caused by fluid compressibility.



Dihedral Angle is the upward angle from horizontal of the wings or tailplane of a fixed wing aircraft. A larger dihedral angle gives greater roll (lateral) stability at the cost of efficiency.



Wing Loading;

Wing Loading = Loaded Weight of Aircraft / Area of the Wing

Operating at a higher wing loading, corresponds to the high landing and take off speeds

Pitch, Yaw and Roll




Pitch is to gain or to lose altitude
Yaw is in the vertical direction
Roll is in the horizontal direction

Elevators are flight control surfaces, usually at the rear of an aircraft which control the aircraft's orientation by changing the pitch of the aircraft.



Rudder controls the yawing motion.



Ailerons are the control surface usually on the trailing edge of the wings and are used to control roll.



Elevons are aircraft surfaces that combine the functions of the elevator and the aileron. Mostly used in flying wings.



AUW (All Up Weight) is the total weight of the aircraft. Also known as Aircraft Gross Weight. Auw decreases during the flight due to fuel and oil comsumption.

Aspect Ratio of a wing is an indicator of the aircrafts roll response.
There are two ways to calculate

Aspect Ratio = Wing Span / Average Chord
Aspect Ratio = (Wing Span)(Wing Span) / Wing Area

Lift Force, a fluid flowing past the surface of a body exerts a surface force on it. Lift is defined to be the component of this force that is perpendicular to the oncoming flow direction.



For calculating the Coefficient of Lift we can use the lifting line theory, which is;


Where AR is Aspect Ratio

Drag Force acts in a direction opposite to the oncoming flow velocity.



For calculating the Coefficient of Drag we can use the lifting line theory, which is;




Where AR is Aspect Ratio