Accession Number : ADA311017

Title :   Evaluation of the Boeing Pan Air Technologies Code (A502i) Through Prediction of Separation Forces on the GBU-24.

Descriptive Note : Master's thesis,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s) : LeTourneau, Matthew A.

PDF Url : ADA311017

Report Date : MAR 1996

Pagination or Media Count : 116

Abstract : The Boeing PAN AIR Technologies code (A502i) is investigated to explore its suitability for determination of separation forces on ordnance. To this end, A502i is first assessed by applying it to three problems for which other solutions and experimental data are available, i.e. steady flow past a rectangular, parabolic arc wing and a delta wing at both subsonic and supersonic conditions. Good agreement is found in all cases. A502i is then applied to the GBU-24's being in two configurations for a subsonic case and a supersonic case. Good agreement is found with data obtained from wind tunnel experiments for low angles of attack.

Descriptors :   *AERODYNAMIC FORCES, *GUIDED BOMBS, *BALLISTIC TRAJECTORIES, COMPUTER PROGRAM DOCUMENTATION, MATHEMATICAL MODELS, ACCURACY, THESES, INPUT OUTPUT PROCESSING, MOMENTS, ANGLE OF ATTACK, FLOW FIELDS, TERMINAL BALLISTICS, BOUNDARY VALUE PROBLEMS, WAKE, JET FIGHTERS, SUBSONIC CHARACTERISTICS, MACH NUMBER, SUBSONIC FLOW, SUPERSONIC FLOW, COMPUTER FILES, AIRCRAFT MODELS, SUPERSONIC CHARACTERISTICS, NAVIER STOKES EQUATIONS, INVISCID FLOW, FREE STREAM, FLOW SEPARATION, WING BODY CONFIGURATIONS, DELTA WINGS, POTENTIAL FLOW, STEADY FLOW, CANARD CONFIGURATIONS.

Subject Categories : Ballistics
      Guided Munitions

Distribution Statement : APPROVED FOR PUBLIC RELEASE