Pls i need the solution in steps to help me practice & follow it. Pls also using pythonxcantera, pls check for accuracy. Thank you

# Input parameters 

opposed-flow ethane/air diffusion flame p = ct.one_atm # pressure tin_f = 300.0 # fuel inlet temperature tin_o = 300.0 # oxidizer inlet temperature mdot_o = 0.72 # kg/m^2/s mdot_f = 0.24 # kg/m^2/s comp_o = 'O2:0.21, N2:0.78, AR:0.01' # air composition comp_f = 'C2H6:1' # fuel composition

Generate a flamelet manifold for a rocket combustion simulation. The flamelet approach, is a popular approach to model combustion. Instead of solving the transport equations of all the species, O(10100), flamelet model only requires to solve several (usually 3 ) scalar transport equations are needed. For this project generate a flamelet manifold that can be used by combustion CFD. The goal is to construct a flamelet manifold to take the inputs -mixture fraction mean (Z), mixture fraction variance (Z), and progress variable mean (C), and able to provide the outputs: species mass fractions ( Yk), temperature ( T), and density (rho ). Progress-variable approach for LES of turbulent combustion y viscosity is given by the Smagorinsky model, t=C2S,whereS=S~ijS~ij subgrid kinetic energy is modelled using q2=Ck2S2, , is the filter width. Note, that the isotropic part of the residual st I to be modelled separately when pressure is decoupled from therm s, because it may then be lumped together with the pressure. In th coustic interactions and compressibility are neglected, so in the it ttional efficiency, this term is not actually computed. zsidual scalar fluxes are modelled as subgrid turbulent scalar flux -diffusion assumption, qik=uki+uki=ti,k, Ie eddy diffusivity is given by t=C2S