Design a Ramjet System with a rectangular supersonic intake as shown below for the following operating parameters: Flight Mach No. M-2.5, Alt-30K ft, Required Thrust 10 KN, Fuel is Octane QR = 50 MJ/Kg, Standard Heat of Formation h (octane) = -249 KJ/mol, h(HO) = -243 KJ/mol, h(CO) = -393.52 KJ/mol and burns in the combustor with the following reaction: CsH18 + x(O+3.76N) 8CO + 9HO + y(O+3.76N) D D Determine the following: 1. Inlet Area, Nozzle throat area, Exit Area, distance D, distance D2, Wedge Angle 2. Total Pressure Recovery at the inlet 3. Combustor Inlet Area for Mach No M = 0.2 4. Combustor Temperature and qman for thermal choking 5. Air Mass Flow rate, Fuel Flow rate & TSFC 6. Exit Velocity Make Suitable assumptions where required and use appropriate fuel-air ratio (ie. Values for x & y in the reaction equation).