The interest in flying wings dates as far the early years of the aviation age. Over the 20th century, numerous attempts were made to investigate the feasibility of the concept, which demonstrated numerous early benefits: increased aerodynamic efficiency, reduced fuel consumption and lower noise and pollutant emissions compared to conventional tube and wing aircraft. However, major technical challenges prevented that type of design from entering mass production, especially with regards to structural design and manufacturing, stability and control and ride quality. In the 1990’s, a new concept, the blended wing body (BWB), was created to alleviate some of the concerns of flying wings while maintaining increased efficiency. Despite the promise, technical hurdles once again proved to be a deal breaker, and as of 2024, the only flying wing to enter serial production is the B-2 Spirit, an extremely complex and expensive aircraft. Thirty years later, as the world is quickly transitioning towards cleaner energy, the interest in the blended wing body has been renewed. The latest technological advancements in the aerospace industry should make the development of the BWB more plausible, however passenger comfort issues remain. Surprisingly, the BWB development may come from an unexpected application: as a tanker aircraft. As the U.S. Air Force is seeking a replacement to hundreds of aging tankers, a startup company was recently funded to develop the concept and build a prototype. In this study, we explore the history of blended designs from its early days, highlighting its opportunities and challenges – and why the design is an intriguing fit for application as a tanker aircraft.

The Blended Wing Body (BWB) configuration is considered to have the potential of providing significant advantages when compared to conventional aircraft designs. At the same time, numerous studies have reported that technical challenges exist in many areas of its design, including stability and control. This study aims to create a novel BWB design to test its flying and handling qualities using an engineering flight simulator and as such, to identify potential design solutions which will enhance its controllability and manoeuvrability characteristics. This aircraft is aimed toward the commercial sector with a range of 3,000 nautical miles, carrying a payload of 20,000kg. In the engineering flight simulator a flight test was undertaken; first, to determine the BWB design’s static stability through a standard commercial mission profile, and then to determine its dynamic stability characteristics through standard dynamic modes. Its flying qualities suggested its stability with a static margin of 8.652% of the Mean Aerodynamic Chord (MAC) and consistent response from the pilot input. In addition, the aircraft achieved a maximum lift-to-drag ratio of 28.1; a maximum range of 4,581 nautical miles; zero-lift drag of 0.005; and meeting all the requirements of the dynamic modes.