Abstract: MIT Lincoln Laboratory operates a number of research aircraft through its Flight Test Facility, including two aircraft as part of a long-running program with the US Air Force. Due to various factors, the current platforms (a Gulfstream II and an HU-25) are planned to be replaced by two Gulfstream IV business jets. As such, MIT Lincoln Laboratory has been undergoing an extensive engineering design and analysis effort to transform these two aircraft from their business jet configurations into research test beds to support the needs of the program. A major aspect of the modification is the addition of hard points for wing stores carriage. As such, accurate flutter prediction is of significant importance to ensure safe operation of the aircraft over a large variety of wing store configurations. The talk will begin with an overview of the program and associated challenges. A detailed discussion of the flutter work will be provided, including: comparison of flutter results using panel method and CFD-based aerodynamics, CFD-based reduced-order flutter modeling discussion and results, and comparison against flight flutter test data. The talk will conclude with a summary and the next steps in the analysis and certification efforts.
Bio: Dr. Nate Falkiewicz is a Technical Staff member in the Structural and Thermal-Fluids Engineering Group at MIT Lincoln Laboratory. Since joining the Laboratory in 2014, he has been involved in the development of a variety of airborne systems and associated capabilities, spanning subsonic through hypersonic speeds. His areas of interest include multidisciplinary modeling & simulation, hypersonics, applied aerodynamics/CFD, aeroelasticity, high performance computing, and automated design/optimization. Prior to joining Lincoln Laboratory, he was a member of the Loads & Aeroelasticity Group at Boeing Research and Technology, where he developed methods for multidisciplinary simulation of hypersonic vehicles, researched advanced methods for aircraft aero-structural optimization, and led the enterprise-wide Aeroelasticity Community of Excellence. He received his Ph.D. in aerospace engineering from the University of Michigan where his research focused on reduced-order aerothermoelastic modeling methods for hypersonic vehicles. He served as a member of the AIAA Structural Dynamics Technical Committee from 2013 - 2020, serves as a reviewer for a number of journals, and is an AIAA Associate Fellow.
(student host will be Cody Karcher)