Paper Titles
Preface
Bamboo Planer Machine Frame Design and Strength Analysis Using Finite Element Method
p.3
Effect of Temperature Setting on 3d Printer Machine for Chocolate Printing
p.11
Prototype Development for Predicting Eccentricity Based on Rotating Unbalanced Behavior of Train
p.17
Numerical Simulation Using Slats, Slots, and Flaps in Steady Flight Conditions
p.23
Developmental Research for Industrial Image Processing in the Engineering Education to Learn SDGs
p.33
Evaluation of Urban Drainage System as a Flood Control in Klitren Urban Village
p.43
Rock Mass Classifications of Flysch Deposits for Analyses of Tunnel Behaviour and Support System-A Case Study of Design Evaluation of Tunnel 6 of Jakarta-Bandung High-Speed Railway
p.49
Application of RMR, Q, and Japanese Rock Mass Classification Systems for Design of Support Systems of the Narogong Weir Diversion Tunnel, West Java, Indonesia
p.59

Numerical Simulation Using Slats, Slots, and Flaps in Steady Flight Conditions

Article Preview

Abstract:

At this time, it has become commonplace for aircraft to use high lift devices. The high lift devices used include flaps, slats, slots, elevators, ailerons, and others. This study examines the effect of multiple elements on the wing, especially the combination of slat slots and flaps in several configurations.. This research was conducted with numerical simulations on wing airfoil NACA 43018. The observed conditions were rectangular wing (no slats, slots, and flaps) compared to the use of slats, slots, and flaps under steady flight conditions. The angles of attack used are (α) = 0o, 2o, 4o, 6o, 8o, 10o,12o,15o, 16o,17o,19o, and 20o. Numerical simulation using Ansys 19.1 application with turbulent model k-ε realizable. The use of slats, slots, and flaps does not result in a shift in the stall point but tends to increase aerodynamic performance (CL/CD)which is very significant. By paying attention to pressure drag, viscous drag and the resulting induced drag, the use of slats, slots, and flaps reduces a large amount of induced drag so that the lift to drag ratio increases.

You might also be interested in these eBooks
Technology for Sustainable Development View Preview

Info:

Periodical:

Advances in Science and Technology (Volume 112)

Pages:

23-31

DOI:

https://doi.org/10.4028/p-d376fs

Citation:

Cite this paper

Online since:

April 2022

Authors:

Setyo S.P. Hariyadi*, Bambang Junipitoyo, Wawan Aries Widodo, Imam Sonhaji, Fungky Dyan Pertiwi

Keywords:

Flap, NACA 43018, Slat, Slot, Steady Flight

Export:

RIS, BibTeX

Price:

Permissions CCC:

Request Permissions

Permissions PLS:

Request Permissions

Сopyright:

© 2022 Trans Tech Publications Ltd. All Rights Reserved

Share:

Citation:

* - Corresponding Author

References

[1] N. Harris McClamroch, Steady aircraft flight and performance, Steady Aircraft Flight and Performance. (2011).

DOI: 10.1515/9781400839063

Google Scholar

[2] L. Zhibo, H. Qitao, J. Hongzhou, L. Hongren, Solving the steady flight state of aircraft based on hybrid genetic algorithm, 2009 2nd International Conference on Information and Computing Science, ICIC 2009. 2 (2009) 200–203. https://doi.org/10.1109/ICIC.2009.159.

DOI: 10.1109/icic.2009.159

Google Scholar

[3] C. Badrya, Title of dissertation : CFD / Quasi-Steady Coupled Trim Analysis of Diptera -type Flapping Wing MAV in Steady Flight Department of Aerospace Engineering, (2016).

DOI: 10.2514/6.2016-3557

Google Scholar

[4] U. Pesavento, Z.J. Wang, Flapping wing flight can save aerodynamic power compared to steady flight, Physical Review Letters. 103 (2009). https://doi.org/10.1103/PhysRevLett.103.118102.

DOI: 10.1103/physrevlett.103.118102

Google Scholar

[5] G. Matič, M. Jankovec, D. Jurman, M. Topič, Feasibility Study of Attitude Determination for All-Rotating Unmanned Aerial Vehicles in Steady Flight, Journal of Intelligent and Robotic Systems: Theory and Applications. 80 (2015) 341–360. https://doi.org/10.1007/s10846-014-0173-z.

DOI: 10.1007/s10846-014-0173-z

Google Scholar

[6] Y. Liu, L. Zhang, J. Shao, Adaptive Control Algorithm for Steady Flight of Mars UAV with Four Rotors, IOP Conference Series: Materials Science and Engineering. 470 (2019). https://doi.org/10.1088/1757-899X/470/1/012039.

DOI: 10.1088/1757-899x/470/1/012039

Google Scholar

[7] C.R. de Cos, J.A. Acosta, Explicit aerodynamic model characterization of a multirotor unmanned aerial vehicle in quasi-steady flight, Journal of Computational and Nonlinear Dynamics. 15 (2020). https://doi.org/10.1115/1.4047388.

DOI: 10.1115/1.4047388

Google Scholar

[8] H. Kamliya Jawahar, S.A. Showkat Ali, M. Azarpeyvand, Serrated slat cusp for high-lift device noise reduction, Physics of Fluids. 33 (2021). https://doi.org/10.1063/5.0035178.

DOI: 10.1063/5.0035178

Google Scholar

[9] A. Shmilovich, Y. Yadlin, E.D. Dickey, A.N. Gissen, E.A. Whalen, Lift Recovery for AFC-Enabled High Lift System, (2017).

Google Scholar

[10] G. Chen, X. Tang, X. Yang, P. Weng, J. Ding, Noise control for high-lift devices by slat wall treatment, Aerospace Science and Technology. 115 (2021) 106820. https://doi.org/10.1016/j.ast.2021.106820.

DOI: 10.1016/j.ast.2021.106820

Google Scholar

[11] J. Ruhland, C. Breitsamter, Numerical analysis of high-lift configurations with oscillating flaps, CEAS Aeronautical Journal. 12 (2021) 345–359. https://doi.org/10.1007/s13272-021-00498-7.

DOI: 10.1007/s13272-021-00498-7

Google Scholar

[12] S. Srivastava, Numerical Analysis of Wings for UAV based on High-Lift Airfoils, 5 (2015) 325–330. https://doi.org/10.13140/RG.2.2.24448.76803.

Google Scholar

[13] D.Z. Lima, J.B. Aguiar, W.G. Ferreira, Preliminary Structural Design of a Fowler Flap High-lifting Device, SAE Technical Papers. (2021). https://doi.org/10.4271/2020-36-0028.

DOI: 10.4271/2020-36-0028

Google Scholar

[14] S.N.V. Neigapula, S.P. Maddula, V.B. Nukala, A study of high lift aerodynamic devices on commercial aircrafts, Aviation. 24 (2020) 123–136. https://doi.org/10.3846/aviation.2020.12815.

DOI: 10.3846/aviation.2020.12815

Google Scholar

[15] N. Mulvany, L. Chen, J. Tu, B. Anderson, Steady-State Evaluation of Two-Equation RANS (Reynolds-Averaged Navier-Stokes) Turbulence Models for High-Reynolds Number Hydrodynamic Flow Simulations, Department of Defence, Australian Government. (2004)1–54. http://oai.dtic.mil/oai/oai?verb=getRecord&metadataPrefix=html&identifier=ADA426359.

Google Scholar

[16] S.H.S. Putro, Sutardi, W.A. Widodo, Numerical study of three-dimensional flow characteristics around the wing airfoil E562 with forward and rearward wingtip fence, in: 2019: p.020017. https://doi.org/10.1063/1.5138272.

DOI: 10.1063/1.5138272

Google Scholar

[17] S.P. Setyo Hariyadi, Sutardi, W.A. Widodo, A. Rachmadiyan, Numerical simulation of airfoil Eppler 562 with variations of whitcomb wingtip devices, in: AIP Conference Proceedings, 2018. https://doi.org/10.1063/1.5046199.

DOI: 10.1063/1.5046199

Google Scholar

[18] B. Günther, F. Thiele, R. Petz, W. Nitsche, J. Sahner, T. Weinkauf, H.C. Hege, Control of separation on the flap of a three-element high-lift configuration, Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting. 5 (2007) 3259–3273. https://doi.org/10.2514/6.2007-265.

DOI: 10.2514/6.2007-265

Google Scholar

[19] F.O.R. Aeronautics, ADVISORY, (1939).

Google Scholar

[20] S.G. Kontogiannis, D.E. Mazarakos, V. Kostopoulos, ATLAS IV wing aerodynamic design: From conceptual approach to detailed optimization, Aerospace Science and Technology. 56 (2016) 135–147. https://doi.org/10.1016/j.ast.2016.07.002.

DOI: 10.1016/j.ast.2016.07.002

Google Scholar