DATA ITEM DESCRIPTION
Title: GAS TURBINE ENGINE STEADY STATE AND TRANSIENT PERFORMANCE
PRESENTATIONS FOR COMPUTER PROGRAMS
Num
ber: DI-MISC-81966 Approval Date: 20140702
AMSC Number: F9484 Limitation: N/A
DTIC Applicable: No GIDEP Applicable: No
Preparing Activity: 11 (AFLCMC/EZFP)
Applicable Forms: N/A
Use/Relationship: Engine steady state and transient computer programs (herein referred to as Models)
provide a detailed description of the aerothermodynamic cycle performance and stability characteristics of
the Propulsion System. These Models will be provided to the Using Service for evaluation of Propulsion
System performance and stability characteristics during source selections, evaluations/studies during the
development program, and post-qualification modification evaluations throughout the life of the program.
This Data Item Description contains the format and content preparation instructions for data resulting
from the work task described by 3.2.1 and 4.2.1 of Aircraft Turbine Engines Joint Service Specification
Guide 2007 (JSSG-2007).
Req
uirements:
1. Reference documents. The applicable issue of the documents cited herein, including their approval
dates and dates of any applicable amendments, notices, and revisions, shall be as specified in the
solicitation or contract.
2. Format. The Models shall be formatted as follows:
2.1 Except as modified herein, the Models shall conform to the Society of Automotive Engineers
Aerospace Standards AS681J, “Gas Turbine Engine Performance Presentation for Computer Programs”
and AS755E, “Aircraft Propulsion System Performance Station Designation and Nomenclature”.
(SAE documents are available from SAE International, 400 Commonwealth Drive, Warrendale PA
15096-0001; 1-877-606-7323; www.sae.org
.)
2.2 The Models shall be written and provided in either FORTRAN or Numerical Propulsion System
Simulation (NPSS) source languages, and shall be capable of being compiled and executed on the
computer system and platform identified by the Using Service.
2.3 The Models shall carry suitable identification including the engine model designation, manufacturer’s
name, engine specification number, revision date, and Model identification number.
2.4 The Models shall be thermodynamic cycle simulations in which component identity is maintained
(i.e., each fan, axial compressor, and centrifugal compressor; each turbine, combustor, augmenter, and fan
duct; and each exhaust nozzle must be identified as entities in the Model logic) as required to obtain and
maintain an accurate simulation.
DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited.
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