Accession Number : ADA129501


Title :   Computer Program for Estimating Stability Derivatives of Missile Configurations - Users Manual.


Descriptive Note : Technical rept.,


Corporate Author : ARMY MISSILE COMMAND REDSTONE ARSENAL AL SYSTEMS SIMULATION AND DEVELOPMENT DIRECTORATE


Personal Author(s) : Sanders,George A ; Washington,W D


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a129501.pdf


Report Date : Aug 1982


Pagination or Media Count : 112


Abstract : This report is intended to be a users manual for a computer program called AERODSN, which estimates the stability coefficients of typical missile configurations with wings or tail fins or both. The Mach range is from zero to approximately 4.0. The roll orientation is zero (plus configuration). Wings and tails must be in line. Control deflections are allowed. A limited amount of body alone experimental data is included (ogive cylinder or cone cylinder); however, body alone tables can be input if desired. A conical boattail segment can be added. This program does not predict drag. Static stability and damping derivatives at zero angle of attack are predicted. (Author)


Descriptors :   *COMPUTER PROGRAMS , *AERODYNAMIC CONFIGURATIONS , *GUIDED MISSILES , *AERODYNAMIC STABILITY , *AERODYNAMIC CHARACTERISTICS , *STATIC STABILITY , COMPUTERIZED SIMULATION , ROLL , PITCH(MOTION) , DAMPING , INPUT OUTPUT PROCESSING , ANGLE OF ATTACK , ESTIMATES , MATHEMATICAL PREDICTION , CYLINDRICAL BODIES , COEFFICIENTS , MACH NUMBER , OGIVES , CONICAL BODIES , WING BODY CONFIGURATIONS


Subject Categories : Computer Programming and Software
      Guided Missiles
      Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE