Aircraft thrust, drag, rate of climb and velocity?

Question

An aircraft has the following property:

Weight = 1720 kN

Wing area = 287 m^2

Span = 47.7m

Oswalds efficency factor = 0.7

Two turbofan engines net thrust = 190kN

Mach number = 0.57

Altitude = 6100 metres

Speed of sound = 316m/s

density = 0.65283 kg/m^3

Find

1. Calculate the thrust and power required assuming L/D is optimum.

2. Calculate the max rate of climb and angle of climb

3. Explain how the max velocity can be obtained and give an estimate at the above altitude.

Im really stuck!

Answer 1

Haha, I don't how. I'm still learning... (not this stuff yet)

Answer 2

Are you asking someone to do your engineering homework for you?  What country are you from?

Answer 3

Calling stacheair,,,,

I guarantee stacheair can explain this to you with out

doing the math for you.