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Study on Effects of Triangular Bumps on Aerodynamic Performance of NACA 0012 Airfoil.

Record Type:	Language materials, manuscript : Monograph/item
Title/Author:	Study on Effects of Triangular Bumps on Aerodynamic Performance of NACA 0012 Airfoil./
Author:	Ding, Feihao.
Description:	1 online resource (46 pages)
Notes:	Source: Masters Abstracts International, Volume: 84-11.
Contained By:	Masters Abstracts International84-11.
Subject:	Mechanical engineering. -
Online resource:	click for full text (PQDT)
ISBN:	9798379553753

Study on Effects of Triangular Bumps on Aerodynamic Performance of NACA 0012 Airfoil.
Ding, Feihao.

Study on Effects of Triangular Bumps on Aerodynamic Performance of NACA 0012 Airfoil. - 1 online resource (46 pages)

Source: Masters Abstracts International, Volume: 84-11.

Thesis (M.S.)--New York University Tandon School of Engineering, 2023.

Includes bibliographical references

There have been several methods to affect aerodynamic performance. This work simulates the effect of a triangular bump on the aerodynamic performance of a NACA 0012 airfoil. The bump is considered a type of vortex generator that has been proven to enhance aerodynamic performance by delaying the boundary layer separation. For this paper, the 5mm, 7.5mm, and 10mm height of the bump was placed at 30%, 50%, and 70% of the chord length. The coefficient of lift and drag in different cases were calculated and evaluated. The L/D ratio was reduced for all cases compared to the smooth case from 27% to 76%. Extensions for further studies are discussed.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2024

Mode of access: World Wide Web

ISBN: 9798379553753Subjects--Topical Terms:

557493
Mechanical engineering.
Subjects--Index Terms:

Aerodynamic performanceIndex Terms--Genre/Form:

554714
Electronic books.

Study on Effects of Triangular Bumps on Aerodynamic Performance of NACA 0012 Airfoil.
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504 $a Includes bibliographical references
520 $a There have been several methods to affect aerodynamic performance. This work simulates the effect of a triangular bump on the aerodynamic performance of a NACA 0012 airfoil. The bump is considered a type of vortex generator that has been proven to enhance aerodynamic performance by delaying the boundary layer separation. For this paper, the 5mm, 7.5mm, and 10mm height of the bump was placed at 30%, 50%, and 70% of the chord length. The coefficient of lift and drag in different cases were calculated and evaluated. The L/D ratio was reduced for all cases compared to the smooth case from 27% to 76%. Extensions for further studies are discussed.
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538 $a Mode of access: World Wide Web
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650 4 $a Physics. $3 564049
650 4 $a Engineering. $3 561152
650 4 $a Aerospace engineering. $3 686400
653 $a Aerodynamic performance
653 $a Airfoil
653 $a Passive flow control
653 $a Vortex generator
653 $a Triangular bump
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