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 f/a=0.03 (c) the exhaust gas mass flow rate me. (d) the gross thrust. (e) the net thrust, (f) the thrust power, (g) the propulsive efficiency n_(p) (h) the thermal efficiency n_(th) (i) the specific fuel consumption q (i) the overall efficiency n_(0)

To solve this problem, we will use the given data and apply the principles of thermodynamics and fluid mechanics. Let's calculate each part step by step.---### **Given Data:**- Flight Mach number - Altitude: - Ambient pressure: - Ambient temperature: - Effective exhaust velocity: - Inlet cross-sectional area: - Fuel-to-air ratio: **Constants:**- Specific gas constant for air: - Ratio of specific heats for air: ---### **(a) Air mass flow rate ( ):**The air mass flow rate is calculated using the continuity equation: where: #### Step 1: Calculate speed of sound ( ): #### Step 2: Calculate flight velocity ( ): #### Step 3: Calculate air density ( ): #### Step 4: Calculate air mass flow rate ( ): So, the air mass flow rate is: ---### **(b) Fuel mass flow rate ( ):**The fuel mass flow rate is related to the air mass flow rate by the fuel-to-air ratio: Rearranging for : So, the fuel mass flow rate is: ---### **(c) Exhaust gas mass flow rate ( ):**The exhaust gas mass flow rate is the sum of the air mass flow rate and the fuel mass flow rate: So, the exhaust gas mass flow rate is: ---### **(d) Gross thrust ( ):**Gross thrust is given by: Substitute the values: So, the gross thrust is: ---### **(e) Net thrust ( ):**Net thrust accounts for the momentum of incoming air: Substitute the values: So, the net thrust is: ---### **(f) Thrust power ( ):**Thrust power is the product of net thrust and flight velocity: Substitute the values: So, the thrust power is: ---### **(g) Propulsive efficiency ( ):**Propulsive efficiency is given by: Substitute the values: So, the propulsive efficiency is: ---### **(h) Thermal efficiency ( ):**Thermal efficiency is given by: Here, is the heat released per unit mass of fuel. Since is not provided in the problem, we cannot calculate without additional information.---### **(i) Specific fuel consumption ( ):**Specific fuel consumption is given by: Substitute the values: So, the specific fuel consumption is: ---### **(j) Overall efficiency ( ):**Overall efficiency is the product of propulsive efficiency and thermal efficiency: Since is not calculated due to missing , cannot be determined without additional information.--- This concludes the solution.