Analysis of Vortex Dominated Flow over Double Delta Wing

Jump To References Section

Authors

  • Department of Power Engineering, Jadavpur University, Kolkata - 700032, West Bengal ,IN
  • Department of Mechanical Engineering, Swami Vivekanada University, Kolkata - 700121, West Bengal ,IN
  • Department of Mechanical Engineering, Jadavpur University, Kolkata - 700032, West Bengal ,IN
  • Department of Power Engineering, Jadavpur University, Kolkata - 700032, West Bengal ,IN

DOI:

https://doi.org/10.18311/jmmf/2023/35861

Keywords:

Lift and Drag Coefficient, Pressure Distribution, Q-Criterion, Strake, Vortices, Wind Tunnel, Wing

Abstract

The maneuverability of fighter aircraft designed using double delta wing configuration at low subsonic speed in addition to under high angle of attacks are highly appealing and fascinating to comprehend. Flow pattern formed by double delta wing help to facilitate lifting force under high angle of attack and at such low subsonic speed. In comparison to delta wing, vortex formations by strake part of wing play an important role to create a persistent vortex core capable of delaying stalling. In this investigation, force coefficients of 75°/45° double delta wing configuration is extracted both from wing tunnel experiment and numerical calculation between 0° to 30° angles of attack at Reynolds number of 1.4 × 105 based on root chord length. It has also been attempted to investigate the flow pattern formation over wing leeward surface, interaction between vortices formed by strake/wing based on Q-criterion and pressure distribution along propagation path of vortices obtained from CFD (Computational Fluid Dynamics) calculations. Implications of interplay between vortices and pressure distribution in lift generation have also been analyzed. It has been found that around 15° angle of attack strake and wing vortices merge and gets more intensified. With higher angle of attack the lift generation significantly diminishes because of vortex bursting

Downloads

Download data is not yet available.

Metrics

Metrics Loading ...

Downloads

Published

2023-12-20

How to Cite

Roy, A., Biswas, S., Prabir Kumar De, & Majumdar, B. (2023). Analysis of Vortex Dominated Flow over Double Delta Wing. Journal of Mines, Metals and Fuels, 71(10), 1620–1630. https://doi.org/10.18311/jmmf/2023/35861

 

References

Cunningham AM, DenBoer RG. Low-speed unsteady aerodynamics of a pitching straked wing at high incidence part II: Harmonic analysis. J Aircraft. 1990 Jan; 27:23-30. DOI: https://doi.org/10.2514/3.56824

Polhamus EC. A concept of the vortex lift of sharp-edge delta wings based on leading-edge suction analogy. NASA Tech. Rep. 1966 Dec.

Verhaagen NG, Jenkins LN, Kern SB. A study of the vortex flow over a 76/40 deg double-delta wing. AIAA paper. 1995. DOI: https://doi.org/10.2514/6.1995-650

Verhaagen NG. Effect of Reynolds number on the flow over 76/40 degree double delta wings. J Aircraft. 2002; 39:1045-1052. DOI: https://doi.org/10.2514/2.3033

Hebbar SK, Platzer MF, Alkhozam AM. Experimental study of vortex flow control on double-delta wings using winglets. J Aircraft. 1996 July; 33:743-751. DOI: https://doi.org/10.2514/3.47010

Sohn M, Chung H. Effect of strake planform change on vortex flow of a double delta wing. J Aircraft. 2007; 44:1842-1848. DOI: https://doi.org/10.2514/1.30261

Heyes AL, Smith DA. Modifications of a wing tip vortex generators. Aerospace Science and Technology. 2005 Sept.; 9:469-475. DOI: https://doi.org/10.1016/j.ast.2005.04.003

Hamidi HE, Rahimi M. Numerical investigation of high attack angle flow on 76/40 degree double-delta wing in incompressible flow. 2011.

Sohn MH, Jang YIL. Visualization and flow field measurements of the vortical flow over a double-delta wing. Int J Aeronaut Space Sci. 2003; 4:63-74. DOI: https://doi.org/10.5139/IJASS.2003.4.1.063

Ekaterinaris JA, Coutley RL, Platzer MF. Numerical investigation of high incidence flow over a double delta wing. J Aircraft. 1995; 32:457-463. DOI: https://doi.org/10.2514/3.46742

Kern SB. Vortex flow control using winglets on a double delta wing. J Aircraft. 1993; 30:818-825. DOI: https://doi.org/10.2514/3.46422

Saha S, Majumdar B. Modeling and simulation on double delta wing. Int J Adv Comput Res. 2003 Mar; 3.

Yuvaprakasah J, Kumar P, Das S, Prasad JK. Experimental and numerical studies on double delta wing with sharp leading edge at subsonic speed. Int Res J Multidiscip Sci Technol. 2016 July; 1.

Hunt JCR, Wray AA, Moin P. Eddies, streams, and convergence zones in turbulent flows. Proc Summer Program. 1988; 193-208.

Holeman V. Methods for vortex identification. Master’s Thesis. 2012 Dec.

Muir RE, Arredondi-Galeana A, Viola IM. The leadingedge vortex of swift wing-shaped delta wings. R Soc Open Sci. 2017 Aug; 4:170077. DOI: https://doi.org/10.1098/rsos.170077

Spalart PR, Allmaras SR. A one equation turbulence model for aerodynamic flows. La Recherche Aerpspatiale. 1994; 1:5-24.

Sohn MH, Chang JW. Effect of a centerbody on the vortex flow over double-delta wing with leading edge extension. Aerospace Sci Technol. 2010 Jan; 14:11-18.x DOI: https://doi.org/10.1016/j.ast.2009.11.004

Most read articles by the same author(s)