Fluid-Structure Interaction Evaluation of F-16 Limit Cycle Oscillations

Application of high-fidelity computational science and engineering (CSE) tools provide better data for decisions to enhance weapon systems acquisition, testing, and support. Fluid structure interaction (FSI) simulation is being evaluated to quantify aero-structural dynamic mechanisms that bound F-16...

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Bibliographische Detailangaben
Hauptverfasser:	Lechniak, Jason A, Bhamidipati, Keerti K
Format:	Report
Sprache:	eng
Schlagworte:	ACQUISITION AEROELASTICITY Attack and Fighter Aircraft COMPUTATIONAL FLUID DYNAMICS Electricity and Magnetism F-16 AIRCRAFT FLIGHT TESTING FLUID FLOW FLUID STRUCTURE INTERACTION FLUTTER FREQUENCY RESPONSE JET FIGHTERS OSCILLATION PHYSICAL PROPERTIES VALIDATION VELOCITY WEAPON SYSTEMS
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Beschreibung
Zusammenfassung:	Application of high-fidelity computational science and engineering (CSE) tools provide better data for decisions to enhance weapon systems acquisition, testing, and support. Fluid structure interaction (FSI) simulation is being evaluated to quantify aero-structural dynamic mechanisms that bound F-16 limit cycle oscillations (LCO). The intent of the research objectives is to provide a better understanding of flight-test aero-structural observations through the utilization of CSE tools. Validation of results provided by CSE tools using experimental testing as the truth source, allows for development of methods and processes to accurately determine coupled-field physical characteristics of full fighter aircraft configurations. Specifically for F-16 LCO, the response frequency, coupled mode response, and flutter/LCO onset velocity are evaluated for comparison of CSE tool results against flight test results.