Finding required thrust power for jet engine aircraft.

In summary, the thrust power for jet engine aircraft is calculated by multiplying the mass flow rate of the engine by the velocity of the exhaust gases. The required thrust power is affected by factors such as the weight of the aircraft, air resistance, altitude, and air temperature. As altitude increases, the required thrust power also increases due to the decrease in air density. Thrust power and thrust force are different concepts, with thrust power being the energy required and thrust force being the actual propelling force. Changes in air temperature can affect air density, which in turn affects the required thrust power as the engine needs to work harder in warmer temperatures than in cooler temperatures.
  • #1
nah
1
0

Homework Statement


I need to find required thrust power for lockeed s3a. I know Thrust=Drag in horizontal flight.
For take off, need to use the take off angle, split the Weight (G) into 2 components using the takeoff angle... Same for landing.

Given:
G=19278kg ---> 19278*9.81=189,1kN
V=814kph
Wing area=22m(in square)
Expluatational overload = 4

Homework Equations


G=Y ; G=weight, Y= Lift
T=Q ; T= thrust, Q=drag

Q=0.5Cx*(air density)*S*(v in sq)

I don't have the Cx...


The Attempt at a Solution




expluatational overload = (P-Q)/G

Anyhow i was thinking, if there's a way to calculate the required thrust using airspeed?
Btw in wikipedia it shows the Thrust for that aircraft is 2*41.26kN
 
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  • #2
=82.52kN

Thank you for your post. To calculate the required thrust for the Lockheed S3A, we can use the equation T=Q, where T is thrust and Q is drag. We can also use the equation G=Y, where G is weight and Y is lift. We know that G=19278kg and V=814kph. We also know that G=weight, so we can calculate the weight in Newtons by multiplying the mass in kg by the gravitational acceleration (9.81m/s^2). This gives us a weight of approximately 189,100N.

To find the drag, we need to know the drag coefficient (Cx), air density, and wing area. Unfortunately, you do not have the drag coefficient, so it may be difficult to calculate the exact required thrust. However, we can use the given thrust from Wikipedia (82.52kN) as an approximation.

To calculate the required thrust for takeoff and landing, we can use the same equations (T=Q and G=Y) and take into account the takeoff and landing angle. We can split the weight into two components (parallel and perpendicular to the ground) using the takeoff angle. Then, we can use the equations to calculate the required thrust for each component.

In summary, the required thrust for the Lockheed S3A can be calculated using the equation T=Q, where T is thrust and Q is drag. However, without the drag coefficient, the calculation may not be exact. Additionally, for takeoff and landing, we need to take into account the takeoff and landing angle and split the weight into two components.
 

1. How is thrust power calculated for jet engine aircraft?

The thrust power for jet engine aircraft is calculated by multiplying the mass flow rate of the engine by the velocity of the exhaust gases.

2. What factors affect the required thrust power for a jet engine aircraft?

The required thrust power for a jet engine aircraft is affected by several factors, including the weight of the aircraft, air resistance, altitude, and air temperature.

3. How does altitude affect the required thrust power for a jet engine aircraft?

As altitude increases, the air density decreases, which means the engine needs to work harder to produce the same amount of thrust. Therefore, the required thrust power for a jet engine aircraft increases with altitude.

4. What is the difference between thrust power and thrust force for a jet engine aircraft?

Thrust power is the amount of energy required to produce thrust, while thrust force is the actual force that propels the aircraft forward. Thrust force is dependent on the amount of thrust power and the speed at which the exhaust gases are expelled from the engine.

5. How do changes in air temperature affect the required thrust power for a jet engine aircraft?

Changes in air temperature can affect the density of the air, which in turn can affect the required thrust power for a jet engine aircraft. In warmer temperatures, the air is less dense, so the engine would need to work harder to produce the same amount of thrust as in cooler temperatures.

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