Flapping wing CFD/CSD aeroelastic formulation based on a corotational shell finite element

Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

Volumn , Issue , 2009, Pages

  Chimakurthi, Satish K ^a   Stanford, Bret K ^b   Cesnik, Carlos E S ^a   Shyy, Wei ^a  

^a UNIVERSITY OF MICHIGAN   (United States)

^b UNIVERSITY OF FLORIDA   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AEROELASTIC RESPONSE; AEROELASTIC SOLVERS; CFD/CSD; COMPUTATIONAL FRAMEWORK; COMPUTATIONAL STRUCTURAL DYNAMICS; CRITICAL COMPONENT; EXPERIMENTAL DATA; FINITE ELEMENT; FLAPPING MOTION; FLAPPING WING; FORWARD FLIGHT; LARGE AMPLITUDE; LARGE ROTATION; LOW REYNOLDS NUMBER; MICRO AERIAL VEHICLE; NAVIER-STOKES SOLVER; PRESSURE-BASED; RECTANGULAR WINGS; SHELL FINITE ELEMENTS; SINGLE DEGREE OF FREEDOMS; SINGLE-AXIS; SMALL STRAINS; VALIDATION STUDY; WING CONFIGURATIONS; WING STRUCTURES;

AERODYNAMICS; AEROELASTICITY; ASPECT RATIO; COMBINATORIAL OPTIMIZATION; COMPUTATIONAL FLUID DYNAMICS; DYNAMICS; INCOMPRESSIBLE FLOW; MICRO AIR VEHICLE (MAV); REYNOLDS NUMBER; STRUCTURAL DYNAMICS;

FLEXIBLE WINGS;

EID: 84855623788     PISSN: 02734508     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

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