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Flow Characteristic of Blunt- edged Delta Wing at High Angle of Attack

Journal of Advanced Research in Fluid Mechanics and Thermal Sciences
Volume 39 No. 1, November 2017, Pages 17-25

Nurulhuda Tajuddin1, Shabudin Mat1,*, Mazuriah Said1, Shumaimi Mansor1
1Department of Aeronatical, Automotive and Offfshore Engineering, Fakulti Kejuruteraan Mekanikal, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
*Corresponding author: shabudin@fkm.utm.my

KEYWORDS

Delta wing, angle of attack, UTM-LST, vortex flow

ABSTRACT

The main objective of this project is to investigate the flow characteristics of the VFE2 blunt edged delta wing profiles at high angle of attack. The vortex is developed on the upper surface of delta wing and this flow physics is very complicated. The vortex flow on the sharp-edged wing develops in the Apex region. Different flow topology is observed for the blunt-edge wing. The vortex on the blunt-edged wing is not developed in the apex region but at a certain cord wise position based on angle of attack, Reynolds number and leading edge bluntness. The primary vortex moved upstream with increasing angle of attack. The problem is that this vortex will be formed up to the apex if the angle of attack is further increased. No data available at higher angle of attack of beyond ? = 30° during the VFE-2 experiments due to the constraint of the experimental work. The data from the surface pressure measurement performed at 1×106 and 2×106 is presented in this paper. The experiments were conducted at Universiti Teknologi Malaysia Low Speed Tunnel (UTM-LST) with maximum speed of 83 m/s. The data were interpreted using pressure coefficient, Cp against distance of pressure tube that based on the delta wing chord. Apart from that, tuft method was also performed to visualize the flow characteristics above the surface of delta wing at high angle of attack. The results highlight interesting flow physics above blunt-edged wing at high angle of attack. The result shows that the primary moves upstream closed the apex at high angles of attack.

CITE THIS ARTICLE

MLA
Tajuddin, Nurulhuda, et al. “Flow Characteristic of Blunt- edged Delta Wing at High Angle of Attack.” Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 39.1 (2017): 17-25.

APA
Tajuddin, N., Mat, S., Said, M., & Mansor, S. (2017). Flow Characteristic of Blunt- edged Delta Wing at High Angle of Attack. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 39(1), 17-25.

Chicago
Tajuddin, Nurulhuda, Shabudin Mat, Mazuriah Said, and Shumaimi Mansor. “Flow Characteristic of Blunt- edged Delta Wing at High Angle of Attack.” Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 39, no. 1 (2017): 17-25.

Harvard
Tajuddin, N., Mat, S., Said, M. and Mansor, S., 2017. Flow Characteristic of Blunt- edged Delta Wing at High Angle of Attack. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 39(1), pp.17-25.

Vancouver
Tajuddin, N, Mat, S, Said, M, Mansor, S. Flow Characteristic of Blunt- edged Delta Wing at High Angle of Attack. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences. 2017;39(1):17-25.

REFERENCES

[1] Hummel, D. (2008). Chapter 17 – The International Vortex Flow Experiment 2 (VFE-2): Objectives and Overview. RTO-TR-AVT-113, Page 17-1 – 17-20.
[2] Luckring, J.M. and Hummel, D. (2008). Chapter 24 – What Was Learned From The New VFE-2 Experiments. RTOTR-AVT-113.
[3] Mat, Shabudin Bin, Richard Green, Roderick Galbraith, and Frank Coton. “The effect of edge profile on delta wing flow.” Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 230, no. 7 (2016): 1252-1262.
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[9] Chu, J. and Luckring, J.M. (1996). Experimental Surface Pressure Data Obtained on 650 Delta Wing across Reynolds Number and Mach number Ranges. NASA Technical Memorandum 4645. (Small-edged report)
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[12] Coton, Frank, Shabudin Mat, Roderick Galbraith, and Robert Gilmour. “Low speed wind tunnel characterization of the VFE-2 wing.” AIAA Paper 382 (2008): 2008.
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