The inlet component represents all types of inlets used for gas turbines. The inlet requires specification of the gas turbine design point inlet air mass flow and specification of pressure loss in the form of the ram recovery factor RR. RR represents the ratio of total pressure at inlet exit (usually fan or compressor entry) divided by free stream (ambient) total pressure. Four options are available for specification of the ram recovery factor:

•MIL-E-5008B standard

RR according to this standard assumes RR=1 up to flight Mach 1. Above Mach 1, RR is reduced using a function of Mach.

Note that the MIL-E-5008B standard relation is scaled to design RR. This means RR values deviating from MIL-E-5008B standard may result if the design RR deviates from the MIL-E-5008B standard at the design Mach number. The Ambient conditions information box in the Design tab sheet indicates design flight Mach number and other ambient condition information.

Warning: A design RR value higher than the MIL-E-5008B standard value (e.g. with design flight Mach number larger than 1) may result in (unrealistic) subsonic RR values higher than 1.

•User specified RR

Both design and off-desing RR are user specified.

•User specified RR design only

Design RR is user specified, off-design RR is corrected assuming linear relation between relative pressure loss (1-RR) and squared corrected inlet massflow.

•RR map

Ram recovery determined by an inlet map. The map file consists of tables with RR as a function of flight mach number and corrected airflow at inlet exit. View the map graph using the Map button in the Map tab sheet.

In the Design tabsheet, design RR / PR can be specified. The Set to MIL Std button can be used to set the design RR to the MIL-E-5008B standard value (function of flight Mach number).