A typical gas turbine combustor has an inlet Mach number of 0.2 and a stagnation pressure loss of 3%. In this problem we will estimate the contributions to the pressure loss of Rayleigh heating and friction (Fanno), assuming properties of low-temperature air. a) The combustor inlet and exit stagnation temperatures are 900K and 1300K, respectively. For Rayleigh flow with inlet (State 3) Mach number of 0.2, determine the % pressure loss (p.3-Pod/p03. b) Assume that the rest of the 3% stagnation pressure loss is due to friction. Modeling the friction as Fanno flow, with an average friction factor f=0.02, find the effective L/D. That is, find the L/D ratio for a constant-area duct with the same frictional stagnation pressure loss as the combustor. The inlet Mach number is still 0.2, but the exit Mach number may differ from part a). [Note: f=0.02 is the Darcy friction factor, equals 4c, in some texts.]