Wing Sweep, Structural Motion and Their Effect on Separation and Transition Simulations, Wind Tunnel and Flight Experiments
Abstract
The main focus of this research is on the effect of sweep on separation and transition for wing sections undergoing structural motion. Sweep angles from zero degrees to 22deg (X 56A) and finally up to 40deg (close to UCAVs) will be considered and the influence of cross flow on laminar boundary layer transition and separation will be investigated. A multi tiered approach consisting of flight experiments, wind tunnel experiments, wing section simulations, highly resolved canonical model problem simulations, and theory will be employed. The proposed research will rely on existing research tools (instrumented 1:3 scale X 56A, flight test infrastructure, wind tunnel equipment, CFD codes) that will be modified to allow for the inclusion of sweep. The combined investigative approach will allow us to cover a large range of Reynolds numbers (in CFD, wind tunnel and flight tests). Fundamental flow physics that are discovered at more moderate Reynolds numbers (200k 500k) can be investigated at larger Reynolds numbers that approach the flight conditions of larger UAVs. Thus, a connection to flight is established which underlines the direct Air Force relevance of the proposed basic research. The anticipated outcomes are guidelines for wing designs with reduced fatigue loads and-or tailored elastic properties that exploit the structural motion for improvements in performance and-or efficiency. The direct benefits are an increase in payload, a considerable reduction of the energy consumption, and a significant increase in range and endurance.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jan 14, 2022
- Source ID
- FA95501910174
Entities
People
- Hermann Fasel
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Arizona