Author: RMApetrei (rmapetrei1@sheffield.ac.uk), JLCuriel-Sosa, NQin
Date: 14/08/2018
---
Contents: This file contains the ANSYS Fluent settings used to run simulations
in transonic flow about the wing-body of the NASA Common Research Model at 
flight conditions of Mach (M) = 0.85 and Reynolds Number (Re) 5.0 million
---

For RSM Turbulence model:
---
Setup:
	General:
		Solver		     : Density-Based
		Velocity Formulation : Absolute
		Time                 : Steady
	Models:
		Multiphase	     : Off
		Energy		     : On
		Viscouse	     : Reynolds Stress, Linear Pressure-Strain, Enhanced Wall Treatment
		Radiation	     : Off
		Heat Exhchanger	     : Off
		Species		     : Off
		Discrete Phase	     : Off
		Acoustics	     : Off
	Materials:
		Fluid		     : air (Density - Ideal Gas, Cp - Ct., Thermal cond. - Ct., Viscosity - power-law)
		Boundary Conditions  :
			Aircraft     : wall
			Symmetry     : symmetry
		        Farfield     : Pressure Farfield 
				Mach Number	        : 0.85
				Turbulence Intensity    : 0.5
				Turbulence Length scale : 0.49
				Temperature		: 300 K
		Operating Conditions : 3798 Pa
	Reference Values:
		Area		     : 191.84 m^2
		Density		     : 0.04410567 kg/m^3
		Enthalpy	     : 345448.7 J/kg
		Length		     : 7.0005 m
		Pressure 	     : 0 Pa
		Temperature	     : 300 K
		Velocity 	     : 295.0245 m/s
		Viscosity	     : 1.7894e-5 kg/ms
		Ratio of Specific Ht : 1.4
---
Solution
	Solution Methods:
		Formulation	     : Implicit
		Flux Type	     : Roe-FDS
		Gradient	     : Least Squares Cell Based
		Flow		     : Second Order Upwind
		Turb. Kinetic Energy : Second Order Upwind
		Turb. Dissip. Rate   : First Order Upwind
		Reynolds Stresses    : First Order Upwind
	Solution Controls:
		Courant Number	     : 1
		Turb. Kinetic Energy : 0.8 (relaxation)
		Turb. Dissip Rate    : 0.8 (relaxation)
		Turb. Viscosity	     : 1 (relaxation)
		Reynolds Stresses    : 0.5 (relaxation)
	Monitors:
		CL, CD, CM monitors defined
	Solution Initialisation:
		Compute from Farfield