Review of variable leading-edge patents for aircraft wings and engine inlets and their relevance for variable pitot inlets in future supersonic transport

Abstract

The motivation for designing variable pitot inlets for future supersonic transport (SST) is explained. A comprehensive overview of existing technological solutions for variable leading edges of aircraft wings and engine inlets is given. The advantages and limitations of over 80 solutions, as well as their relevance for application on variable pitot inlets for SST are described. The challenges of existing solution options concerning design methodologies, level of detail, and experience with a technology are identified.

Conceptual Design and Evaluation of Air Inlets of Fuel Cell-Powered Electric Aero Engines for Regional Aircraft

“…3. For turbofan engines, pitot inlets are the preferred option [9]. However, they must be located at the front of a nacelle.…”

“…A variable geometry inlet can adapt to changing air mass flow requirements and flight conditions, potentially enhancing total pressure ratios during take-off and reducing spillage drag compared to fixed-geometry inlets. Various mechanisms serve this purpose [9]:…”