Answer:
The lift coefficient is 0.3192 while that of the moment about the leading edge is-0.1306.
Explanation:
The Upper Surface Cp is given as

The Lower Surface Cp is given as

The difference of the Cp over the airfoil is given as

Now the Lift Coefficient is given as

Now the coefficient of moment about the leading edge is given as

So the lift coefficient is 0.3192 while that of the moment about the leading edge is-0.1306.
Answer:
option B is correct. Fracture will definitely not occur
Explanation:
The formula for fracture toughness is given by;
K_ic = σY√πa
Where,
σ is the applied stress
Y is the dimensionless parameter
a is the crack length.
Let's make σ the subject
So,
σ = [K_ic/Y√πa]
Plugging in the relevant values;
σ = [50/(1.1√π*(0.5 x 10^(-3))]
σ = 1147 MPa
Thus, the material can withstand a stress of 1147 MPa
So, if tensile stress of 1000 MPa is applied, fracture will not occur because the material can withstand a higher stress of 1147 MPa before it fractures. So option B is correct.
Answer:
True
Explanation:
The CNC is the primary interface between the machine operator and the machine.