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

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Abstract

The drag coefficient of the nacelle lip-skin model was investigated to analyze the aerodynamic performance of the bias acoustic liner underneath the nacelle lip-skin at lowspeed free stream velocities. Drag coefficient reduction, using the bias flow of a bias acoustic liner on a nacelle lip-skin, is discussed for incompressible flow condition. The experimental data were recorded to analyze the nacelle lip-skin’s drag coefficients. The investigation covered four different bias flow areas to total nacelle lip-skin area ratios, ranging from 0 % to 12 %, at Reynolds numbers ranging from 2.2×105 to 3.5×105 and the nacelle internal static pressure of 0- 90 Pa, with the uncertainty of the experimental data being less than 10 %. The results show that the drag coefficient is reduced by up to 19 % as the ratio of the bias flow area to the total nacelle lip-skin area increases from 0 % to 12 %. In the transition flow regime, the drag coefficient increases gradually with Reynolds number. In addition, the optimum nacelle internal static pressure of present study was found to be 60 Pa.

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Abbreviations

A :

Effective area of nacelle

AL:

Acoustic liner

A LIP :

Area of the nacelle lip-skin

A BAL :

Total surface area covered by all the holes

BAL:

Bias acoustic liner

C D :

Drag coefficient

F :

Blowing fraction

F D :

Drag force

I :

Length of the D-chamber

LIP :

Nacelle lip-skin

MBT:

Micro blow technique

P D :

Dynamic pressure

P b :

Nacelle internal static pressure

PTAI:

Piccolo tube anti-icing

Re:

Reynolds number

SAI:

Swirl anti-icing

v :

Free stream velocity

v b :

Velocity of bias flow

μ :

Dynamic viscosity of air

ρ :

Density of air

ε :

Uncertainty

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Acknowledgments

The authors acknowledge funding from the Ministry of Higher Education Malaysia and University Sains Malaysia’s Fellowship and Fundamental Research Grant Scheme (203.PMEKANIK. 6071411).

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Authors and Affiliations

  1. School of Mechanical Engineering, Universiti Sains Malaysia, Penang, 14300, Malaysia

    Lee Chern Khai & Mohd Azmi Ismail

  2. School of Aerospace Engineering, Universiti Sains Malaysia, Penang, 14300, Malaysia

    Qummare Azam & Nurul Musfirah Mazlan

Authors
  1. Lee Chern Khai
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  2. Mohd Azmi Ismail
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  3. Qummare Azam
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  4. Nurul Musfirah Mazlan
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Corresponding author

Correspondence to Mohd Azmi Ismail.

Additional information

Recommended by Editor Yang Na

Lee Chern Khai received the Bachelor’s in Aerospace Engineering from Universiti Sains Malaysia, Engineering campus, Nibong Tebal, Penang, Malaysia. His areas of expertise are heat transfer, anti- Icing, CFD and nanofluids.

Mohd Azmi Ismail received the Bachelor’s and Master’s in Mechanical Engineering from Universiti Sains Malaysia, Engineering campus, Nibong Tebal, Penang, Malaysia. His Doctorate is from Kingston University, United Kingdom. His areas of expertise are electronic cooling, anti-Icing, spillway dams, CFD and air-conditioning.

Qummare Azam received the Bachelor’s in Mechanical Engineering from ICFAI University, Dehradun in 2014, India. He is currently pursuing a Ph.D. by research in Aerospace Engineering at Universiti Sains Malaysia, Engineering campus, Nibong Tebal, Penang, Malaysia.

Nurul Musfirah Mazlan received her Doctorate in Aerospace Propulsion Engineering from Cranfield University, U.K. She is currently a Lecturer in the Department of Aerospace Engineering, Universiti Sains Malaysia, Engineering campus, Nebong Tebal, Malaysia. Her expertise is in bio-fuel, aircraft engine performance and aircraft combustion.

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Khai, L.C., Ismail, M.A., Azam, Q. et al. Experimental study on aerodynamic performance of nacelle lip-skin bias flow. J Mech Sci Technol 34, 1613–1621 (2020). https://doi.org/10.1007/s12206-020-0323-0

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  • DOI: https://doi.org/10.1007/s12206-020-0323-0

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