A ramjet engine operates at a flight Mach number M_(0)=0.8 at 9000 m altitude where p_(0)=30.14 kPa and T_(0)=229K For an effective exhaust velocity V_(e)=760m/s and inlet cross-sectional area A_(1)=0.187m^2 calculate; (a) the air mass flow rate m_(0) (b) the fuel mass flow rate my for a fuel-to-air ratio of ffa=0.03 (c) the exhaust gas mass flow rate me. (d) the gross thrust, (e) the net thrust, (f) the thrust power, (8) the propulsive efficiency n_(p) (h) the thermal efficiency 7_(th) (i) the specific fuel consumption q (i) the overall efficiency n_(o)

(a) The air mass flow rate can be calculated using the formula: where is the air density at the inlet, is the inlet cross-sectional area, and is the inlet velocity.To find , we can use the ideal gas law: where is the inlet pressure, is the specific gas constant for air, and is the inlet temperature.Substituting the given values, we get: Now, we can calculate : (b) The fuel mass flow rate can be calculated using the formula: Substituting the given fuel-to-air ratio and the calculated air mass flow rate , we get: (c) The exhaust gas mass flow rate is the sum of the air and fuel mass flow rates: (d) The gross thrust can be calculated using the formula: Substituting the given exhaust velocity and the calculated inlet velocity , we get: (e) The net thrust can be calculated using the formula: Substituting the calculated values, we get: (f) The thrust power can be calculated using the formula: Substituting the calculated values, we get: (g) The propulsive efficiency can be calculated using the formula: Substituting the given exhaust velocity and the calculated inlet velocity , we get: (h) The thermal efficiency can be calculated using the formula: Substituting the given exhaust velocity and the calculated inlet velocity , we get: (i) The specific fuel consumption can be calculated using the formula: Substituting the calculated fuel mass flow rate and the net thrust , we get:$q = \