T-MATS: Nozzle Library Block
This block simulates the performance of a nozzle using thermodynamic equations, properties, table lookups, and Cantera functions. To utilize this block a Cantera object must exist in the workspace as a global variable named fs, which may be created with the Cantera importPhase command. The fs variable must include all Species defined in the file canteraload.m.

Nozzle Inputs:

Nozzle Input	Description
Flow In	Flow Data Input, 25x1 vector consisting of: -1- W - gas path flow [pps] -2- s - entropy [BTU/(lbm*degR)] -3- Tt - total temperature [degR] -4- Pt - total pressure [psia] -5- ht - total enthlapy [BTU/lbm] -6- rhot - total density [lbm/ft3] -7- gamt - total specific heat ratio -8- Ts - static temperature [degR] -9- Ps - static pressure [psia] -10- hs - static enthalpy [BTU/lbm] -11- rhos - static density [lbm/ft3] -12- gams - static specific heat ratio -13- Vflow - flow velocity [ft/sec] -14- MN - Mach number -15- A - flow area [in2] -16to21- species array values, defined in canteraload.m -22to25- future use
Pamb	Ambient static Pressure [psia]

Nozzle Outputs:

Nozzle Output	Description
Flow Error	Flow Error [frac], in a typical system this will be driven to zero by an iterative solver
Fg	Gross thrust [lbf]
N_Data	Nozzle internal calculation Data

Nozzle Mask Variables:

Nozzle Mask Variable	Description
Ath_in_M	Nozzle Throat Area [in^2]
Cfg_M	Nozzle thrust Coefficient
iDes_M	Design fork (0, 1, 2) 0 - Calculate nozzle throat area based on design variables When iDesign is set to 0, Ath_in_M from the General tab will not be used. Throat area calculated will be saved to the workspace. 1 - Nozzle throat area variables are taken from the workspace. When iDesign is set to 1, Ath_in_M from the General tab and the Design values from the iDesign tab will not be used. 2 - Nozzle throat area from the General tab will be used in the nozzle module. When iDesign is set to 2, Ath_in_M from the General tab will be used; Design values from the iDesign tab will not be used.
Wdes_M	Design flow[pps]