Effect of Steady Spanwise Blowing on the Aerodynamic Coefficients of a Maneuverable Aircraft Wing Model

Document Type : Research Article

Authors

1 Aerospace Engineering Faculty, Shahid Sattari Aeronautical University of Science And Technology, Tehran, Iran

2 Department of Mechanical Engineering, KNTU, Tehran, Iran

Abstract

In this study, the effect of steady spanwise blowing on the aerodynamic coefficients of a maneuverable aircraft wing model has been simulated three dimensionally applying the fluent software. The simulations have been performed at the Mach number of 0.4 and different angles of attack, using unstructured grid and the (k−ω SST) turbulence model. Numerical simulation results showed that the spanwise blowing along the wing leading edge caused a flow along the axis of leading edge vortex and delayed the vortex breakdown until the high angles of attack. As a result, the lift coefficient increases at higher angles of attack, which is directly related to the jet momentum coefficient. By apply blowing, due to the vortex breakdown on the wing surface, drag coefficient is greater in comparison to the no blowing condition until the angle of attack 24 degrees and after this angle, the drag coefficient decreases. Also, drag coefficient decrease is lower at greater jet momentum coefficients. By injecting the flow over the wing, the vortex increases in different longitudinal sections and causes a greater pressure drop on the upper surface of the wing. Also, the greatest amount of pressure in the inner span of the wing and near the edge of the wing attack is observed.

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References

[1]  C. Dixon, Lift augmentation by lateral blowing over a lifting surface, VTOL Research, Design, and Operations Meeting, 1969, pp. 193.
[2]  J. Cornish, High lift applications of spanwise blowing, The Seventh Congress of the International Council of the Aeronautical Sciences, 1970, pp. 14-18.
[3]  C. Dixon, J. Theisen, R. Scruggs, Theoretical and Experimental Investigations of Vortex Lift Control by Spanwise Blowing, Volume I. Experimental Research, Lockheed-Georgia Co Marietta Light Sciences Div, 1973.
[4]  K.P. Clarke, Lift augmentation on a moderately swept wing by spanwise blowing, The Aeronautical Journal, 80(790) (1976) 447-451.
[5]  G. Brès, D. Williams, T. Colonius, Numerical Simulations of Natural and Actuated Flow over a 3-D, Low-Aspect-Ratio Airfoil, 40th Fluid Dynamics Conference and Exhibit, 2010, pp. 4713.
[6]  R. Bradley, W. Wray, A conceptual study of leadingedge-vortex enhancement by blowing, Journal of aircraft, 11(1) (1974) 33-38.
[7]  K. Tadakuma, S. Aso, Y. Tani, Active Control of Aerodynamic Characteristics of Space Transportation System by Lateral Blowing, 34th AIAA Fluid Dynamics Conference and Exhibit, 2004, pp. 2718.
[8]  G.E. Erickson, Effect of Spanwise Blowing on the Aerodynamic Characteristics of the F-5E, Journal of aircraft, 16(10) (1979) 695-700.
[9]  G.E. Erickson, Effect of spanwise blowing on the aerodynamic characteristics of a half-span 500 swept cropped delta wing configuration, AIAA Aircraft Systems and Technology Metting, 1979, pp. 1-12.
[10]  J.F. Campbell, Effects of spanwise blowing on the pressure field and vortex-lift characteristics of a 44 deg swept trapezoidal wing.[wind tunnel stability tests-aircraft models], (1975).
[11] M. Ghoreyshi, A. Jirasek, S. Brandt, R. Osteroos, R. Cummings, From spreadsheets to simulation- based aircraft conceptual design, 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2012, pp. 393.
Amirkabir Journal of Mechanical Engineering
Volume 52, Issue 11
February 2021
Pages 3001-3014

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