A rocket nozzle is designed to operate isentropically at 20 km with a chamber with stagnation pressure of 2.0 MPa and temperature of 3000 K. If the products of combustion are assumed to behave as a perfect gas with constant specific heats (y = 1.3 and MW = 20 kg/kmol), determine the design thrust for a nozzle throat area of 0.25 m². Hint: Thrust, T = m Volk + Por.

Aturning operation is performed with following conditions: rake angle of 12°, a feed of 0.35 mm/rev, and a depth of cut of 1.1 mm. the work piece is aluminum alloy 6061 with t6 heat treatment (a16061-t6). the resultant chip thickness was measured to be 1.0 mm. estimate the cutting force, fc. use shear stress of 207 mpa and coefficient of friction on the tool face of 0.6.