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######## Data_Propeller_Rear$_g:# Propeller Rear  			
let Np$_g:=0.9;			# Isentropic Efficiency
let ht$_g:=0.4;			# Hub T Tip Ratio 
let r2max$_g:=4;		# Maximum Radius (meters)
let M_tip_max$_g:=1.0;	# Maximum Tip Mach Number

let M_pff$_g:=0.5;		# Axial Mach number at the propeller
let M_tip$_g:=0.9;		# Propeller Tip Mach Number 
let M$_g:=0.8;			# Exit Mach Number
let rp$_g:=1.1;			# Pressure Ratio Accross Propeller
let m$_g:= 0.01; 		# Mass Flow (kg/s)			
let T$_g:=220;			# Total Temperature Out(Kelvin)
let P$_g:=23000;		# Total Pressure Out(Pascal)
let r2$_g:=2.0;			# Outer Diameter (meters)
let cp$_g:=1005;		# Specific Heat at Constant Pressure (J/kg/Kelvin)
let gam$_g:=1.4;		# Ratio of Specific Heats
let V_prop$_g:=250;		# Propeller Exit Velocity (m/s) 
let A_prop$_g:=20;		# Cross-Sectional Area (m^2)
let omega$_g:=1000;		# Angular Velocity (rad/s)
let W$_g:=-1000000;		# Ppwer Output (Watts)
let thrust[$_g]:=10000;	# Thrust (Newton)

