Question

Consider a venturi with a throat to inlet area ratio of 0.8, mounted on the side of an airplane fuselage. The airplane is in flight at standard sea level. If the static pressure at the throat is 2100 lb/ft^2. Calculate the velocity of the airplane. (Standard sea level density, pressure and viscosity are 1.23 kg/m^3 (0.002377 slug/ft^3 ), 1.01 x 10^5 N/m^2 (2116 lb/ft^2 ) and 1.73 x 10^-5 N-s/m^2 (3.737 x 10^-7 lb-s/ft^2 respectively.

Answer 1

v = 154.703 ft/s

Step-by-step explanation:

given data

throat to inlet area ratio = 0.8

static pressure at the throat p = 2100 lb/ft²

pressure p1 = 2116 lb/ft²

density = 0.002377 slug/ft³

solution

we get here velocity that is express as

v =
`\sqrt{(2(p1-p))/(\rho ((A1)/(At))^2 -1 )}` .................1

put here calculate and we get

v =
`\sqrt{(2(2116-2110))/(0.002377 ((1)/(0.8))^2 -1 )}`

solve it we get

v = 154.703 ft/s