Accession Number : ADP005916

Title :   Prediction of Dynamic Derivatives,

Corporate Author : DORNIER SYSTEM G M B H FRIEDRICHSHAFEN (GERMANY F R)

Personal Author(s) : Fuchs, Heinz ; Kapp, Rolf

Report Date : APR 1988

Pagination or Media Count : 41

Abstract : Dynamic derivatives are introduced by their mathematical definition derived from the general expansion of aerodynamic functions with respect to the relevant independent fluid motion variables. The common classification of dynamic derivatives is evaluated in accordance with the definition used in flight mechanical applications. This is shown with examples of nonstationary motion types creating dynamic derivative effects. This paper shows some basic aspects of a semiempirical method for calculating dynamic derivatives of missile configurations or military aircraft. Results of Dornier's DYNAM computer program 'DYNAM', are presented in comparison with experimental results of different test rigs. This program is based on the 'USAF Stability and Control Datcom' and is updated by semiempirical methods. With assumptions of attached-flow conditions, at small and moderate angles-of-attack the results are for subsonic speeds derived from potential theory and for supersonic speeds from linearized theory. There are also nonstationary panel methods which are useful for determination of dynamic derivativa of harmonic oscillating wings or wing-rudder systems.

Descriptors :   *DERIVATIVES(MATHEMATICS), *AERODYNAMIC CONFIGURATIONS, COMPUTER PROGRAMS, GUIDED MISSILES, MILITARY AIRCRAFT, AERODYNAMIC CHARACTERISTICS, MATHEMATICAL PREDICTION, SUBSONIC CHARACTERISTICS, SUPERSONIC CHARACTERISTICS, CROSS FLOW, AERODYNAMIC DRAG, COEFFICIENTS, SLENDER BODIES, WINGS, OSCILLATION, PRESSURE DISTRIBUTION, GUIDED MISSILE COMPONENTS, TEST FACILITIES, DYNAMIC TESTS, TEST EQUIPMENT, WEST GERMANY.

Subject Categories : Fluid Mechanics
      Test Facilities, Equipment and Methods
      Guided Missile Dynam, Config & Cntrl Surfaces

Distribution Statement : APPROVED FOR PUBLIC RELEASE