Blended Wing Aerodynamic Research

In this study, a blended wing body (BWB) aircraft model was designed, and will be fabricated and tested with the objective of maximizing aerodynamic efficiency as well as determining if boundary layer ingestion from top surface mounted engines results in less drag. The purpose of this study is to prove that BWB aircraft designs are more efficient than traditional cylindrical fuselage and wing designs. Wind tunnel testing as well as computational fluid dynamic (CFD) analysis is expected to support this hypothesis. Both of these tasks are to be completed or are currently in progress. Drag reduction from boundary layer ingestion as well as a more aerodynamic body are the two focus points of this project. Showing that both of these factors are improved by using a BWB design (and thus result in less energy required to fly) is the goal of this study

Blended Wing Aerodynamic Research

Society of Women Engineers Research Committee In this study, a blended wing body (BWB) aircraft model was designed, and has been fabricated and tested with the objective of maximizing aerodynamic efficiency as well as determining if boundary layer ingestion from top surface mounted engines results in less drag. The purpose of this study is to prove that BWB aircraft designs are more efficient than traditional cylindrical fuselage and wing designs. Wind tunnel testing as well as computational fluid dynamic (CFD) analysis has been done to support this hypothesis. Drag reduction from boundary layer ingestion as well as a more aerodynamic body are the two focus points of this project. Showing that both of these factors are improved by using a BWB design (and thus result in less energy required to fly) is the goal of this study

MP-1: Liquid Oxygen & Ethanol Rocket Engine by Mercury Propulsion

Mercury Propulsion is an undergraduate engineering team whose members hold different majors as offered from the College of Engineering at Embry-Riddle Aeronautical University in Prescott, Arizona. The team is tasked to design, build, instrument, and test a liquid rocket engine utilizing an optional Ejector Thrust Augmentation System (ETAS). The engine will burn liquid oxygen and ethanol as its propellants and be designed to produce 200 lb of thrust without augmentation. The end goal of the project is to produce thrust data from two five-second hot-fire tests; one with and one without the ETAS installed. Ignite Grant Awar