Question

tIn a test experiment on a model aero plane in a wind tunnel , the flow speeds on the upper

and lower surfaces of the wing are 70ms

-1

and 63ms-1

respectively. What is the lift on the

wing if its area is 2.5 m

2

? Take the density of air as 1.3 kgm-3

.​​

Answer 1

QUESTION:

A test experiment on a model aero plane in a wind tunnel , the flow speeds on the upperand lower surfaces of the wing are 70ms-1 and 63ms-1 respectively. What is the lift on the wing if its area is 2.5 m^2 ?

Take the density of air as 1.3 kgm-3.​​

Answer:

Speed of wind on the upper surface of the wing, V1​=70m/s

Speed of wind on the lower surface of the wing, V2​=63m/s

Area of the wing, A=2.5m2

Density of air, ρ=1.3kg/m3

According to Bernoullis theorem, we have the relation:

P1+(1/2)ρ(V12​)=P2+(1/2)ρ(V22​)

P2−P1=(1/2)ρ(V12​−V22​)

Where,

P1= Pressure on the upper surface of the wing

P2= Pressure on the lower surface of the wing

The pressure difference between the upper and lower surfaces of the wing provides lift to the aero plane.

Lift on the wing =(P2−P1)A

                          =(1/2)ρ(V12​−V22​)A

                          =(1/2)1.3[702−632]2.5

                          =1512.87

N=1.51×103 N

Therefore, the lift on the wing of the aero plane is 1.51×103 N

Explanation:

tnk u  :)