Experimental study on aerodynamic performance of nacelle lip-skin bias flow

Khai, Lee Chern; Ismail, Mohd Nazari; Azam, Qummare; Mazlan, Nurul Musfirah

doi:10.1007/s12206-020-0323-0

Cited by 6 publications

(6 citation statements)

References 18 publications

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“…Other than that, the other property which influenced in this experimental study is utilized 1.172kg/m 3 , 1.15868 x 10 -5 m 2 /s and 26.8°C, which represented the density, viscosity, and temperature for this research, respectively. Besides, the air flow in this experimental research was assumed to be laminar flow as the Re for the experimental model was conducted much smaller than Re 500,000 [4]. Next, Figure 3 and Figure 4 showed the setup of the experiment work, respectively.…”

Section: Methodsmentioning

confidence: 99%

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The Aerodynamic Characteristics Investigation on NACA 0012 Airfoil with Owl’s Wing Serrations for Future Air Vehicle

Ramli

Mohamed²,

Yusoff³

et al. 2023

ARFMTS

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Owls have an incredibly unique ability to fly in silence, and this ability has significant potential to reduce noise pollution from aircraft engines. For decades, researchers have been studying the noise abatement system in conventional aircraft, but only a few of them had looked into the owl’s ability to reduce the aircraft noise level, especially on the serrated wing. The present study aims to investigate the lift and drag coefficient of the serrated wings including leading-edge serrations, trailing-edge serrations, both-edge serrations, and the original/baseline wing model from the NACA 0012 airfoil. The experimental testing was performed in a wind tunnel at Reynolds numbers of 20,000 and 40,000 and angle of attack from 2° to 30°, in 2° angle intervals. In general, the results showed that each wing model produced a similar lift and drag coefficient profiles, which were proportional to the angle of attack. At Reynolds number of 40,000, the lift coefficient increases from 0.45 to 1.5, as the angle of attack increases from 2° to 24°. Afterward, it decreased as the angle of attack exceeded 24°. According to the data, the trailing-edge serrations model showed the lowest drag coefficient at a Reynolds number of 40,000. Meanwhile, the highest lift coefficient at Reynolds number of 40,000 had been produced by the baseline wing model. This result is beneficial in reducing the noise generation produced by wing structure and at the same time enhancing aerodynamic efficiency.

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Section: Methodsmentioning

confidence: 99%

“…Thus, bias acoustic liner (BAL) has been introduce to overcome noise and ice accretion problems [3]. Moreover, the bias flow from BAL reduces drag coefficient of the nacelle and aircraft [4].…”

Section: Introductionmentioning

confidence: 99%

The Aerodynamic Characteristics Investigation on NACA 0012 Airfoil with Owl’s Wing Serrations for Future Air Vehicle

Ramli

Mohamed²,

Yusoff³

et al. 2023

ARFMTS

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“…In this technique, thermal energy is transferred to the nacelle lip skin as well as a wing in modern commercial aviation (Khai et al, 2020). This energy evaporates the impinging water, a consequence of keeping the surface temperature above freezing.…”

Section: Thermal Ice Protection Systemmentioning

confidence: 99%

Integrating Ice Protection and Noise Abatement Systems for Aircraft Application: A Review

Munas,

Kok Hwa,

Yusoff

et al. 2023

JST

Self Cite

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Aircraft icing remains a key aviation hazard as the global fleet of aircraft in various sectors continues to expand, posing a serious threat to flight safety. As previously stated, the growth of this type of aircraft has been accompanied by an increase in noise levels, and aircraft is reportedly the second most bothersome noise source after traffic. However, integrating an acoustic liner with anti-icing techniques on the leading edge of a nacelle would not efficiently eliminate forward radiated noise and improve the thermal performance of the anti-icing system. Hence, it is of the utmost importance to research the integration of ice protection and noise abatement systems for aircraft applications. This review discusses the integration of ice accretion and noise abatement systems in aircraft applications. The prominence of this review is to explain significant features such as ice protection systems, Computational Fluid Dynamics in ice protection, noise abatement systems, and the integration of ice protection systems and noise abatement systems wherever they are described.

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“…However, the CFD studies require validation of experimental work to ensure its reliability as carried out by many previous researchers. Lee et al, [5] investigated aerodynamic performance of bias acoustic liner for nacelle application. Bahtia et al, [6] employed wind tunnel in China to study the boundary layer for different leading edge geometries.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study of Rigid and Flexible Tandem Wing for Micro Aerial Vehicle

Mohamed

Ismail

Ramli

et al. 2021

ARFMTS

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Unmanned aerial vehicle is becoming increasingly popular each year. Now, aeronautical researchers are focusing on size minimization of unmanned aerial vehicle, especially drone and micro aerial vehicle. The lift coefficient of micro aerial vehicle has wing dimension of 12 cm and mass of less than 7 g. In the present study, with the aid of 3D printer, polylactic acid material was used to develop the micro aerial vehicle structure for tandem wing arrangement. The materials for rigid wing skin and flexible wing skin were laminating film and latex membrane, respectively. The present work elaborates the lift coefficient profiles on rigid wing skin and flexible wing skin at wing flapping frequency of 11 Hz, three different Reynolds numbers of 14000, 19000 and 24000, and five different angles of attacks between 0° and 50°. According to the results obtained, the lift coefficient decreased as the Reynolds number increased. The lift coefficient increased up to 9 as the angle of attack increased from 0° to 50° at the Reynolds number of 14000 for flexible wing skin. The results also showed that the lift coefficient of flexible wing skin was higher than that of rigid wing skin at the attack angle of10° and below, except for the Reynolds number of 14000.

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Experimental study on aerodynamic performance of nacelle lip-skin bias flow

Cited by 6 publications

References 18 publications

The Aerodynamic Characteristics Investigation on NACA 0012 Airfoil with Owl’s Wing Serrations for Future Air Vehicle

The Aerodynamic Characteristics Investigation on NACA 0012 Airfoil with Owl’s Wing Serrations for Future Air Vehicle

Integrating Ice Protection and Noise Abatement Systems for Aircraft Application: A Review

Experimental Study of Rigid and Flexible Tandem Wing for Micro Aerial Vehicle

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