Flight Testing of Mission Adaptive Compliant Wing

TLDR

The MAC‑Wing technology offers lightweight, low‑power, seamless variable‑geometry reshaping of both flap surfaces, with preliminary drag results indicating promising aerodynamic performance and future applications. The study aims to evaluate the flight performance of a Mission Adaptive Compliant Wing and optimize its variable‑geometry flap to maximize laminar boundary‑layer extent across a wide lift‑coefficient range for endurance aircraft. The wing was optimized for laminar boundary‑layer extension and tested at full‑scale dynamic pressure, Mach, and reduced‑scale Reynolds numbers on Scaled Composites’ White Knight aircraft. Flight tests confirm laminar flow up to ~60% chord, enabling a 15% or greater range extension, fuel and weight savings, and increased control authority for endurance aircraft.

Abstract

This paper describes flight test results of a “Mission Adaptive Compliant Wing” (MACWing) variable geometry trailing edge flap in conjunction with a natural laminar flow airfoil. The MAC-Wing technology provides lightweight, low power, variable geometry reshaping of the upper and lower flap surface with no seams or discontinuities. In this particular program, the airfoil-flap system is optimized to maximize the laminar boundary layer extent over a broad lift coefficient range for endurance aircraft applications. The expanded “laminar bucket” capability allows the endurance aircraft to significantly extend their range (15% or more) by continuously optimizing the wing L/D throughout the mission. The wing was tested at full-scale dynamic pressure, full scale Mach, and reduced-scale Reynolds Numbers on Scaled Composites’ White Knight aircraft. Test results confirmed laminar flow regime up to approximately 60% chord for much of the lift range. Analysis and test results suggest significant fuel savings, weight savings and a higher control authority. Preliminary drag results, future aerodynamic applications and vehicle performance projections are discussed.