Aerodynamics of a Prandtl Idealized Blended-Wing Body Subsonic Transport Aircraft
Faculty Mentor Name
Shigeo Hayashibara
Format Preference
Poster
Abstract
The Blended Wing Body (BWB) configuration offers significant aerodynamic efficiency improvements over conventional tube-and-wing aircraft, particularly for long-range transport at high-subsonic cruise conditions. Prior research has demonstrated the benefits of optimized spanwise lift distributions and propulsion-airframe integration, but these factors are often studied independently.
This project investigates how a Prandtl Bell-spanload-inspired lift distribution influences the aerodynamic performance of a transport-class BWB and how these effects interact with representative propulsion-integration concepts. A baseline BWB configuration and a modified Bell-spanload-inspired configuration are analyzed using a combined computational and experimental approach. Low- and high-fidelity computational fluid dynamics (CFD) are used to evaluate lift, drag, and pitching-moment trends, while targeted wind-tunnel testing and flow visualization provide experimental validation and insight into separation behavior and surface flow characteristics.
The study compares aerodynamic performance between configurations and evaluates the effects of different propulsion placements, including pylon-mounted, semi-embedded, and fully ducted concepts. Results will provide experimentally informed insight into spanload shaping strategies for tailless transport aircraft and establish a validated baseline for future high-fidelity and multidisciplinary BWB research. Findings are expected to support development of an AIAA-style conference paper and continued aerodynamic investigation.
Aerodynamics of a Prandtl Idealized Blended-Wing Body Subsonic Transport Aircraft
The Blended Wing Body (BWB) configuration offers significant aerodynamic efficiency improvements over conventional tube-and-wing aircraft, particularly for long-range transport at high-subsonic cruise conditions. Prior research has demonstrated the benefits of optimized spanwise lift distributions and propulsion-airframe integration, but these factors are often studied independently.
This project investigates how a Prandtl Bell-spanload-inspired lift distribution influences the aerodynamic performance of a transport-class BWB and how these effects interact with representative propulsion-integration concepts. A baseline BWB configuration and a modified Bell-spanload-inspired configuration are analyzed using a combined computational and experimental approach. Low- and high-fidelity computational fluid dynamics (CFD) are used to evaluate lift, drag, and pitching-moment trends, while targeted wind-tunnel testing and flow visualization provide experimental validation and insight into separation behavior and surface flow characteristics.
The study compares aerodynamic performance between configurations and evaluates the effects of different propulsion placements, including pylon-mounted, semi-embedded, and fully ducted concepts. Results will provide experimentally informed insight into spanload shaping strategies for tailless transport aircraft and establish a validated baseline for future high-fidelity and multidisciplinary BWB research. Findings are expected to support development of an AIAA-style conference paper and continued aerodynamic investigation.