A fast mail delivery drone uses an ideal jet-propulsion cycle to fly in air of free-stream temperature T1=303K at speed v1=86ms1. The inlet, compressor, turbine, and nozzle flows are isentropic. The engine uses q34 =267kJkg1 of specific heat in the combustor and the tailpipe exit nozzle is choked. By making cold-airstandard assumptions, estimate the specific thrust. State your answer in Nskg1 to zero decimal places and enter the numerical value only