T-MATS: Static Calculation Library Block
This Block calculates static pressure and temperature from an input flow stream and either an assumed throat area or mach number.

StaticCalc Inputs:

StaticCalc Input	Description
GasPthCharIn	Gas Path Characteristics Input, 5x1 vector consisting of: - W - gas path flow [pps] - ht - enthalpy [BTU/lbm] - Tt - Total Temperature [degR] - Pt - Total Pressure [psia] - FARc - Combusted Fuel to Air Ratio [frac]

StaticCalc Outputs:

StaticCalc Output	Description
SOutBus	Static Output Bus, 5x1 vector consisting of: - Ts - Static Temperature [degR] - Ps - Static Pressure [psia] - rhos - Static rho [lbm/ft3] - MN - Mach Number [frac] - Ath - Throat Area [in2]

StaticCalc Mask Variables:

StaticCalc Mask Variable	Description
ST_M	Solve Type: unchecked - Assumed Ath checked - Assumed MN
Ath_M	Assumed Ath [in^2]
MN_M	Assumed Mach Number[frac]
X_FARVec_M	Fuel to Air Ratio Vector (X-axis) (cx1)
Y_TtVec_M	Total Temperature Vector (Y-axis for Gamma calc)(dx1)
T_RtArray_M	Gas Constant, R, Array (R = f(FAR))(cx1)
T_gammaArray_M	Gamma Array (Gamma = f(Tt,FAR))(dxc)