Propellants enter a rocket combustion chamber with a volume of 1.20 m3 at a constant rate of 45.0 kg/s. After they burn, their temperature rises to 2600 K and the molecular weight of the burned products is 9.42 kg/kmol. The nozzle downstream of the combustion chamber limits the exiting mass flowrate to p·8.20 × 10−6 kg/(Pa·s), where p is the pressure in the combustion chamber. If the combustion chamber is at a pressure of 44.0 bar, what is the density of the combustion products in the combustion chamber? You can assume that the products are ideal gases at these high temperature conditions.