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######## Fan_DTC$_g:				# Fan Ducted to Core									
let Nf$_g:=0.9;						# Isentropic Efficiency
let M_eff$_g:=0.4;					# Axial Mach number in front of the fan for civilian turbofans (Raymer, Aircraft Design: A conceptual Approach) 
let M_tip$_g:=1.2;					# Maximum Tip Mach Number
let ht$_g:=0.3;						# Hub to tip ratio of fan (typical value was used)

let rf$_g:=1.3;						# Pressure Ratio																			
let W$_g:=-1000000;					# Power Output (Watt) 
let omega$_g:=150;					# Angular Velocity (Rad/s)
let m$_g:=150;						# Mass Flow (kg/s)		
let To$_g:=275;						# Total Temperature Out (Kelvin)
let Po$_g:=45000;					# Total Pressure Out(Pascal)
let cp$_g:=1005;					# Specific Heat at Constant Pressure (J/kg/Kelvin)
let gam$_g:=1.4;					# Ratio of Specific Heats

let thrust[$_g]:=0;

let D_$_g_1:=150;					# Design Guess
let D_$_g_2:=150;					# Design Guess
let D_$_g_3:=1.3;					# Design Guess
let D_$_g_4:=0.5;					# Design Guess
let D_$_g_5:=0.9;					# Design Guess
let D_$_g_6:=246;					# Design Guess
let D_$_g_7:=35000;					# Design Guess