Answer:
hello your question is incomplete attached below is the complete question
A) optimum compressor ratio = 9.144
B) specific thrust = 2.155 N.s /kg
C) Thrust specific fuel consumption = 1670.4 kg/N.h
Explanation:
Given data :
Mo = 2.1 , To = 220k , Tt4 = 1700 k, hpr = 42000 kj/kg, Cp = 1.004 kj/ kg.k
γ = 1.4
attached below is the detailed solution
Answer:
what kind of content? I need to know
Please add more details because I don’t know if you are using a book or passage, therefore I cannot help you unless you add more detail
Answer:
Part a: The yield moment is 400 k.in.
Part b: The strain is 
Part c: The plastic moment is 600 ksi.
Explanation:
Part a:
As per bending equation

Here
- M is the moment which is to be calculated
- I is the moment of inertia given as

Here
- b is the breath given as 0.75"
- d is the depth which is given as 8"



The yield moment is 400 k.in.
Part b:
The strain is given as

The stress at the station 2" down from the top is estimated by ratio of triangles as

Now the steel has the elastic modulus of E=29000 ksi

So the strain is 
Part c:
For a rectangular shape the shape factor is given as 1.5.
Now the plastic moment is given as

The plastic moment is 600 ksi.
Answer:
You can create high drag which allows a steeper angle without increasing your air speed on landing. you can reduce the length of landing role. Flaps are also used to increase the drag they are retracted when they are not needed. it is adviseable to down he flaps during the time of take off.