Title

Vortex Induced Lift Augmentation: Case Study

Presenter Information

Mariana Escalona Diaz

Department

Mechanical and Aerospace Engineering

Major

Mechanical and Aerospace Engineering

Research Advisor

Finaish, Fathi

Advisor's Department

Mechanical and Aerospace Engineering

Funding Source

Missouri S&T Opportunities for Undergraduate Research Experiences (OURE) Program

Abstract

Optimizing the aerodynamic characteristics of an aerospace vehicle has always been of great importance. For instance, improving the lift-to-drag ratio could represent savings in fuel consumption, an increment in the range & endurance of the aircraft and a shorter take-off and landing distances. Therefore, this study explores the possibility of enhancing the aerodynamic performance by introducing a single step configuration in any given airfoil. The results presented here, use a computational fluid dynamics approach to simulate the development of flow around four different airfoils (NACA 0006, NACA 0009, NACA 1408, and NACA 1410) which utilize a single backward facing step configuration on either the upper or lower curve of the airfoil. All the cases studied, were simulated for two different angles of attack (0⁰ and 5⁰). It was found that the lower step configuration yielded to an increment in lift at lower angles of attacks that enhanced aerodynamic performance of a propeller driven aircraft up to a 130%.

Biography

Mariana is a senior at the Missouri University of Science and Technology. She hopes to graduate in May 2012 with a BS in both Mechanical and Aerospace Engineering. Currently, she is a peer learning assistant in the Physics Department for the Learning Enhancement Across Disciplines (LEAD) program.

Research Category

Engineering

Presentation Type

Oral Presentation

Document Type

Presentation

Award

Engineering oral presentation, Second place

Location

Ozark Room

Presentation Date

06 Apr 2011, 10:30 am - 11:00 am

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Apr 6th, 10:30 AM Apr 6th, 11:00 AM

Vortex Induced Lift Augmentation: Case Study

Ozark Room

Optimizing the aerodynamic characteristics of an aerospace vehicle has always been of great importance. For instance, improving the lift-to-drag ratio could represent savings in fuel consumption, an increment in the range & endurance of the aircraft and a shorter take-off and landing distances. Therefore, this study explores the possibility of enhancing the aerodynamic performance by introducing a single step configuration in any given airfoil. The results presented here, use a computational fluid dynamics approach to simulate the development of flow around four different airfoils (NACA 0006, NACA 0009, NACA 1408, and NACA 1410) which utilize a single backward facing step configuration on either the upper or lower curve of the airfoil. All the cases studied, were simulated for two different angles of attack (0⁰ and 5⁰). It was found that the lower step configuration yielded to an increment in lift at lower angles of attacks that enhanced aerodynamic performance of a propeller driven aircraft up to a 130%.