Finding required thrust power for jet engine aircraft.

[nah]

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

 

[mark726]

=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.