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Experimentation of Aileron and Flap of Airplane Wing Span at Subsonic Speed

Author(s):

Shreyas Navin Bhandari , MIT-WPU; Swapnil Wadkar, MIT-WPU

Keywords:

Subsonic Flow, Pressure Difference, Wing Span, Aileron, Flap

Abstract

Research on Aileron and Flaps and all the parts of the wing span is crucial as the need for fuel consumption is increasing in modern era. Reduction of gas emissions (CO2, NOx), noise and fuel consumption are becoming fundamental design criteria for future aircraft, especially with the high growth rate of air travel which is estimated to double in the coming 20 years. Many airplane accidents have occurred in past years due to improper opening of flaps and aileron during the take-off, landing & rolling. This experiment will be carried out to determine the pressure variations before air striking wing span & after the air strike when the angle of attack on aileron & flap is changed respectively. This will help us to understand the force on the wing when there change in angle of attack of aileron & flaps of wing span. All possible angle of attacks on the parts of wing span will be analyzed. The Reynolds number regime currently studied corresponds to low Reynolds number, laminar and nominally two-dimensional wake. The wing span used for experiment is L=762 mm, C=150 mm with NACA 0012 airfoil type. To control the Cd & Cl on the wing will be the major goal of this experiment. Results are presented for various X/C, Cd, Cl with different angle of attack.

Other Details

Paper ID: IJSRDV7I21424
Published in: Volume : 7, Issue : 2
Publication Date: 01/05/2019
Page(s): 1787-1790

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