Authors Index

[A] [B] [C] [D] [E] [F] [G] [H] [I] [J] [K] [L] [M] [N] [O] [P] [Q] [R] [S] [T] [V] [W] [X] [Y] [Z]

Author	Manuscripts
TAEHYOUN KIM University of Washington Bothell, USA	232 Prediction of Limit Cycle Oscillations Based on Dynamic Eigen Decomposition of Flight Test Data
Christoph Kaiser DLR, Institute of Aeroelasticity	112 A general solver for the prediction of flutter and buffet onset 54 Effect of Turbulent Wedges on the Steady and Unsteady Aerodynamics of a Forward Swept Laminar Wing 123 Analysis of Linearized Motion- and Gust-Induced Airloads with a Next-Generation Computational Fluid Dynamics Solver
Seung-Hoon Kang Seoul National University	135 Machine learning-based parametric model order reduction for the gust load analysis
Kees Kapeteijn DNW	147 Design of a High Aspect Ratio Windtunnel Model for Transonic Gust Load Alleviation
Mordechay Karpel Karpel Dynamic Consulting Ltd.	170 Aeroelastic challenges in the clean aviation hybrid-electric regional aircraft project
Marlus Kerninski Embraer	159 Wind tunnel flutter test results comparison with computational results of a half-span wing
Thiemo Kier	116 Lessons Learned from Flight Testing Active Flutter Suppression Technologies 103 Aeroservoelastic models for design, testing, flight test clearance and validation of active flutter suppression control laws 119 Flutter flight testing: Using operational modal analysis to identify, track and predict flutter for safe and efficient flight test campaigns 141 Assessment of Active Load Control Approaches for Transport Aircraft – Simulation and Wind Tunnel Test 190 Contribution of the ground vibration tests for the preparation of flutter suppression flight test campaigns: Case of the flipased P-Flex UAV 99 Flexible aircraft conceptual co-design based on the RCE framework 128 Post-flight system identification and aeroservoelastic model updating for prediction and validation of the onset of flutter
Thiemo M. Kier German Aerospace Center (DLR), Institute of System Dynamics and Control	107 Wind Tunnel Testing Active Gust Load Alleviation of a Flexible Wing
Spyridon Kilimtzidis University of Patras	199 Application of the unsteady compressible source and doublet panel method to flutter calculations
Thomas Klimmek German Aerospace Center (DLR)	90 The Effect of Aspect Ratio Variation on the Preliminary Aeroelastic Assessment of a Mid-Range Transport Aircraft
Johannes Knebusch DLR German Aerospace Center	215 Improvement of Helicopter Fuselage Modelling - Effects of subcomponents on the overall dynamic behavior 49 Research shake test on an Airbus helicopter technology demonstrator
Christopher Koch German Aerospace Center (DLR), Institute of Aeroelasticity	50 Influence of blade elasticity and thrust on the whirl flutter stability of a propeller-driven aircraft 18 Whirl flutter analysis using linearized propeller transfer matrices
Martin Kolar Czech Aerospace Research Centre (VZLU)	56 New Design of Whirl Flutter Aeroelastic Demonstrator
Raymond Kolonay United States Air Force Research Laboratory	12 Including Gradient-based Transient Gust Optimization in ASTROS
Ramesh Konatala	103 Aeroservoelastic models for design, testing, flight test clearance and validation of active flutter suppression control laws 128 Post-flight system identification and aeroservoelastic model updating for prediction and validation of the onset of flutter
Vassilis Kostopoulos University of Patras	199 Application of the unsteady compressible source and doublet panel method to flutter calculations
Wolf Krueger DLR	147 Design of a High Aspect Ratio Windtunnel Model for Transonic Gust Load Alleviation
Wolf R. Krueger DLR Institute of Aeroelasticity	7 Assessment of aeroelastic stability of high aspect wing aircraft during the preliminary design 141 Assessment of Active Load Control Approaches for Transport Aircraft – Simulation and Wind Tunnel Test
Eduardo Krupa Embraer	159 Wind tunnel flutter test results comparison with computational results of a half-span wing
Wolf R. Krüger German Aerospace Center (DLR) - Institute of Aeroelasticity	121 Design, manufacturing and identification of an active controlled flexible wing for subsonic wind tunnel testing 58 Wind tunnel testing and modal validation of TU-Flex's high aspect-ratio wings 106 Design and Experimental Characterization of a Gust-Generator Concept with Rotating-Slotted Cylinders in the Low-Speed Wind Tunnel DNW-NWB
Wolf Krüger	142 Nonlinear dynamic response of a pazy wing variant using Koiter-Newton model reduction

[A] [B] [C] [D] [E] [F] [G] [H] [I] [J] [K] [L] [M] [N] [O] [P] [Q] [R] [S] [T] [V] [W] [X] [Y] [Z]