subject : propulsion system.. may i get a clear handwriting solution please

Q: An aircraft flies with 280m/s at an altitude of 20km, where ambient pressure and temperature are 26.5kPa and 223.16K, respectively. The jet speed, pressare, and temperature are 600m/s,750K, and 30kPa, respectively. The propulsion system of the aircraft consumes 200kg/s of air and burns 6kg/s of fuel having a heating value of QA=42600kJ/kg. Calculate : 1. The specific thrust (T/ma) 2. The propulsive efficiency (nx) thermal efficiency (nin), and overall efficiency (n0). 3. TSFC 4. The exhaust Mach number (Y=4/3,R=287J/KgK)