Table of Contents
- 1 What weights are included in basic empty weight?
- 2 What is regulated take off weight?
- 3 Is the lift coefficient constant?
- 4 How is MZFW calculated?
- 5 How do you calculate lift force?
- 6 What type of measurement is used to designate the arm in weight and balance computation?
- 7 How do you calculate the lift capacity of an aircraft?
- 8 What is the formula to calculate the weight of an airplane?
What weights are included in basic empty weight?
Standard empty weight (GAMA)—aircraft weight that consists of the airframe, engines, and all items of operating equipment that have fixed locations and are permanently installed in the aircraft, including fixed ballast, hydraulic fluid, unusable fuel, and full engine oil.
What determines the lift coefficient?
The lift coefficient Cl is equal to the lift L divided by the quantity: density r times half the velocity V squared times the wing area A. The lift coefficient then expresses the ratio of the lift force to the force produced by the dynamic pressure times the area.
What is regulated take off weight?
Regulated Take Off Weight – The maximum weight in which an aircraft can take off from a particular runway under specific conditions (winds, weather, specific aircraft configuration, etc,).
What is coefficient of lift aviation?
The lift coefficient (CL) is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area. A lifting body is a foil or a complete foil-bearing body such as a fixed-wing aircraft.
Is the lift coefficient constant?
There is a rather clever way that aerodynamicists group information about airfoils. We have seen that lift changes linearly with area, density, camber, and small angles, and as the square of the velocity. Lift = constant x (geometric stuff) x (flight stuff) x area x angle of attack. …
What is the difference between empty weight and basic empty weight?
Note that basic empty weight includes no usable fuel, but full oil. Empty weight is the weight of the standard airplane, full hydraulic fluid, and undrainable oil. Licensed empty weight, therefore, includes the standard airplane, optional equipment, full hydraulic fluid, unusable fuel, and undrainable oil.
How is MZFW calculated?
Zero Fuel Weight is the weight of the aircraft with everything loaded for that flight, minus useable fuel (Takeoff Weight minus weight of useable fuel).
How do you calculate lift coefficient of lift?
The lift formula is lift force, F = CL × q × A , where CL is lift coefficient, A is area, and q is dynamic fluid pressure.
How do you calculate lift force?
The modern lift equation states that lift is equal to the lift coefficient (Cl) times the density of the air (r) times half of the square of the velocity (V) times the wing area (A).
How much does a a320 weigh?
AirBus A320 Specs
| Airbus A318 | |
|---|---|
| Maximum Zero Fuel Weight(MZFW) | 54,500 kg (120,200 lb) |
| Maximum Landing Weight(MLW) | 57,500 kg (127,000 lb) |
| Maximum Take-off Weight(MTOW) | 68,000 kg (150,000 lb) No NEO Version |
| Takeoff Distance(Sea Level ISA)MTOW | 1,828 Metres (5,997 Feet) |
What type of measurement is used to designate the arm in weight and balance computation?
35 Cards in this Set
| When computing weight and balance, an airplane is considered to be in balance when | The average moment arm of the loaded airplane falls within its CG range |
|---|---|
| What type of measurement is used to designate arm and weight and balance computation? | Distance |
How do you find the lift coefficient from the lift equation?
This equation is simply a rearrangement of the lift equation where we solve for the lift coefficient in terms of the other variables. The lift coefficient Cl is equal to the lift L divided by the quantity: density r times half the velocity V squared times the wing area A .
How do you calculate the lift capacity of an aircraft?
An aircraft’s lift capabilities can be measured from the following formula: d = density of the air. This will change due to altitude. These values can be found in a I.C.A.O. Standard Atmosphere Table.
How do you calculate lift from angle of attack term?
So let’s combine the geometric stuff and the angle of attack term into a new variable called the lift coefficient –> Cl. The original equation then looks like: Lift = constant x Cl x density x velocity squared x area.
What is the formula to calculate the weight of an airplane?
L = (1/2) d v 2 s CL. L = Lift, which must equal the airplane’s weight in pounds. d = density of the air. This will change due to altitude.