Abstract
Objectives: To study the performance of a Modified Co Flow Jet (MCFJ) aerofoil with a converging nozzle located at the leading edge so as to reduce the pumping power. Methods: The experimental investigations are conducted on a base aerofoil and a modified CFJ (MCFJ) aerofoil in a subsonic tunnel at various angle of attack (AOA). The output performance parameters like coefficient of Lift (CL), Coefficient of drag (CD) and Lift are obtained for both the aerofoil and the results are compared. Findings: The result shows that the stalling angle of the MCFJ aerofoil advanced by 5◦ providing better flow characteristics than the baseline aerofoil. The lift increases up to 43% during the critical angle of attack of 25◦ in the MCFJ aerofoil. Novelty: In the present study, a convergent nozzle is placed near the leading edge of the CFJ aerofoil which effectively controls the mass flow rate of the flow during all phases of flight, thereby resulting in improved aerodynamic performance. Applications: This novel concept can be used for improved aerodynamic performance of MCFJ aerofoil with reduced pumping power. Also, it is possible to obtain improved performance of CFJ Method at all phases of flight by controlling the flow velocity by using the convergent nozzle. Keywords: Modified co-flow jet; Angle of attack; Coefficient of lift; Coefficient of lift and drag; Aerodynamic performance
Highlights
During the past few decades there has been an increased interest in improving the performance of the aircrafts by reducing the weight and increasing the aerodynamic performance
The aerodynamic performance of the baseline NACA 6415 and the modified aerofoil Modified Co Flow Jet (MCFJ) using a nozzle is performed and the following results are obtained: 1. The lift generated by the modified co flow jet aerofoil analyzed in this study yielded more lift in the range of 17% to 43% than the baseline aerofoil for various angle of attack considered in this analysis
The drag produced by the modified co flow jet aerofoil is more for low angle of attack and is minimum (~ 15%) for higher angle of attack
Summary
During the past few decades there has been an increased interest in improving the performance of the aircrafts by reducing the weight and increasing the aerodynamic performance. Co-Flow Jet (CFJ) is a recent technique widely used to increase the performance of the aircraft wing as well as increase the stalling angle of attack. The CFJ system necessitates the injection hole to be minimum providing a low velocity jet during take-off and landing whereas the injection hole to be larger providing increased flow at the cruise condition of flight which may not be practically possible. This disadvantage is overcome by the introduction of a convergent nozzle to provide the additional flow over the aerofoil. Nozzle flow can be maintained constant so that the Airf oil lift to drag ratio (L/D) performance of the aerofoil can be improved drastically throughout the stages of the flight
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