Modern gas turbine engines operate at fuel-to-air ratios of about 0.02, pressure ratios (ratio of compressor exit pressure to inlet pressure) of nearly 40, and with a turbine inlet temperature (combustor exit temperature) of about 1800 K. At this condition, the gas mixture exiting the combustor comprises about 4% CO2, 4% H2O, 77% N2, and 15% O2 (in mole percentages). Calculate the average properties of the gas exiting the combustor, specifically molecular weight, M, density, , heat capacity, cp (see Appendix II), and sound speed, a. Since we often approximate this gas as heated air, compare these values with corresponding values for air at 1800 K.