A rocket thrust chamber contains a propellant of molecular weight M = 25 and a specific heat ratio of ? = 1.2. The chamber pressure is pc = pt = 10 MPa, and the combustion temperature is Tc = Tt = 3000 K. The throat area is A? = 0.1 m2 . Determine the thrust for the following conditions:

MPa psia Exhaust area, [m] 0.1 1 0 0 23 0 0 4.06 0.101 14.7 0.1 3 0.101 14.7 4.06 Table 1: Table of values for Problem 1.