2021
DOI: 10.18186/thermal.871989
|View full text |Cite
|
Sign up to set email alerts
|

Aerodynamic Study of Slotted Flap for Naca 24012 Airfoil by Dynamic Mesh Techniques and Visualization Flow

Abstract: Slotted flap is one of high lift devices. It considered as a moving part of the airfoil which is used as a control instrument in a form of elevator, rudders and ailerons. The main focus of work is to investigate the effect of flap chord, gap and overlap on aerodynamic characteristic of NACA 24012 airfoil. The model was tested with 20% C, 30% C and 40% C single slotted flaps at zero angle of attack. The dynamic mesh and user defined function is applied to control the flap distance with respect to wing at any po… Show more

Help me understand this report

Search citation statements

Order By: Relevance

Paper Sections

Select...
2
1
1
1

Citation Types

1
5
0

Year Published

2022
2022
2024
2024

Publication Types

Select...
4
2
1

Relationship

0
7

Authors

Journals

citations
Cited by 8 publications
(6 citation statements)
references
References 11 publications
1
5
0
Order By: Relevance
“…This indicates that the greater the addition of the flap angle, the more the resulting C D value will increase. This pattern is similar to the research conducted by Hussein et al [14]. This is caused by increasing the flap angle, the greater the outer cross-section which is perpendicular to the direction of airflow.…”
Section: Coefficient Of Dragsupporting
confidence: 90%
“…This indicates that the greater the addition of the flap angle, the more the resulting C D value will increase. This pattern is similar to the research conducted by Hussein et al [14]. This is caused by increasing the flap angle, the greater the outer cross-section which is perpendicular to the direction of airflow.…”
Section: Coefficient Of Dragsupporting
confidence: 90%
“…The main concern for this study is to get the, flow visualization and determined the aerodynamic characteristics of the wing for supersonic speed. The sweep angle is varied of 0°, 20°, 40° and 60° deg, the wing has a chord length of 1𝑚 with NACA 2412 airfoils is extruding by 2.8 m. Because the wing has a symmetric geometry, so only a one half of the swept wing is needed to understand the physical phenomena of air flow at supersonic speeds, as well as flow visualization [20].…”
Section: Resultsmentioning
confidence: 99%
“…Therefore, a vortex generator is applied to the surface. In previous years, vortex generators have been studied by many experts including Kharge et al [1], Velte et al [2], Hussein et al [3] etc.…”
Section: Tonsmentioning
confidence: 99%