Venturi throat diameter is 20 mm with coefficient if discharge of 0.85, Fuel orifice diameter is 1.25 mm with coefficient of fuel flow of 0.66; the fuel surface is 5 mm below the throat. Compute:

1) Air fuel ratio for depression of 0.07 bar when nozzle lip is neglected

2) Air fuel ratio when nozzle lip is considered.

Given data: ${d_v} = 0.022m$, $Av = \pi \times 0.0222/4 = 3.80 \times 10 - 04$, ${C_{dv}} = 0.85$, ${d_n} = 0.0125m$, ${A_n} = \pi \times 0.001252/4 = 1.2272 \times 10 - 06$, ${C_{dn}} = 0.66$, $X = 0.005mm$,

Assuming ${\rho _a} = 1.2\frac{{kg}}{{{m^3}}}$ ,${\rho _f} = 750\frac{{kg}}{{{m^3}}}$ ,${P_1} - …