A rocket nozzle has a chamber pressure of 20 Bar (2 MPa) and a chamber temperature of 2750 K. The rocket is designed to operate isentropically at 12,500 m altitude. Note that the pressure at 12,500 m can be estimated using this equation P/P0 = exp [- g (z - z0)/gc/R/T]. You may assume a mean atmospheric temperature of 247 K for this equation. Determine the design thrust for a throat area of 0.1 m2. Assume that k = 1.4 and MW = 20.