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:
exit temperature 285 K
Explanation:
given data
temperature T1 = 270 K
velocity = 180 m/s
exit velocity = 48.4 m/s
solution
we know here diffuser is insulated so here heat energy is negleted
so we write here energy balance equation that is
0 = m (h1-h2) + m × .....................1
so it will be
.....................2
put here value by using ideal gas table
and here for temperature 270K
h1 = 270.11 kJ/kg
solve it we get
h2 = 285.14 kJ/kg
so by the ideal gas table we get
T2 = 285 K
