Flow visualization of the wing model equipped with load control fluidic devices

• Autorzy: Krzysiak A.

Identyfikatory

DOI

10.5604/12314005.1165980

• Języki publikacji: EN

Abstrakty

EN

In the extraordinary off-design flight conditions, such as accelerated manoeuvres or sudden gusts, wing-bending moments may grow rapidly. This may lead to damage of the wing structure. To alleviate the excessive aerodynamic loads in off-design conditions the wing-load-control systems basing on blowing devices were developed. Proposed in these work fluidic devices could be an alternative to the conventional mechanical solutions, such as symmetrical deflections of ailerons or deflection of spoilers. As a result of the CFD studies, among many considered concepts, three solutions were chosen as the most promising. Two of them, namely Fluidic Spoiler and Dual Trailing Edge Nozzles, were tested in IoA low speed wind tunnel. Fluidic Spoiler consisted of the matrix of mini nozzles located on an upper wing surface in its tip part. Air jets blown from the nozzles were influencing the main flow around the wing, leading to flow separation and as a result, to alleviation of wing bending moment. Dual Trailing Edge Nozzles system consisted of the specially shaped nozzles, located at a wing trailing edge. The system utilises the Coanda effect to change a flow circulation around the wing, leading to spanwise redistribution of aerodynamic loads. The paper presents results of the flow visualization tests carried out on the half wing model equipped with load control fluidic devices. Flow visualization was performed using a fluorescent threads illuminated with ultraviolet light. The main objective of the research was to determine the flow separation areas and its character, associated with additional air blowing on the wing surface. The experimental tests were performed in low speed wind tunnel T-3 (5-meter diameter test section) in the Institute of Aviation. For these tests the model of semi-span wing (2.4 m span), situated vertically on the endplate in wind tunnel test section was used. Wind tunnel test were performed at Mach number M = 0.1. The study was carried out in the framework of the European project STARLET.

Słowa kluczowe

EN

applied aerodynamics; load control; fluidic devices

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2015
• Tom: Vol. 22, No. 3
• Strony: 117--124
• Opis fizyczny: Bibliogr. 15 poz., rys.

Twórcy

autor

Krzysiak A.

• Institute of Aviation (IoA) Krakowska Avenue 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 363, fax: [phone]

Bibliografia

• [1] Gad-el-Hak, M., Flow Control – Passive, Active, and Reactive Flow Management, Cambridge University Press, 2000.
• [2] Wygnanski, I., A wind tunnel investigation of a thin airfoil with a sharp leading edge and blowing applied at mid-chord at two angles relative to the surface, Journal of the Royal Aeronautical Society, Vol. 70, No. 666, 1966.
• [3] McLachlan, B. G., Study of the circulation control airfoil with leading/trailing edge blowing, Journal of Aircraft, Vol. 26, pp. 817-821, 1989.
• [4] Braslow, A. L., Burrows, D. L., Tetervin, N., Visconte, F., Experimental and theoretical studies of area suction for control of the laminar boundary layer on an NACA 64A010 airfoil, NACA Report 1025, 1951.
• [5] Bushnell, D. M., Tuttle, M. H., Survey and bibliography on attainment of laminar flow control in air using pressure gradient and suction, NASA RP-1035, 1979.
• [6] Johnston, J., Nishi, M., Vortex generator jets – means for flow separation control, AIAA Journal, Vol. 28, No. 6, pp. 989-994, 1990.
• [7] Krzysiak, A., Control of flow using self-supplying air jet vortex generators, AIAA Journal, Vol. 46, No. 9, pp. 2229-2234, 2008.
• [8] Schlichting, H., The boundary layer with suction and injection, Luftfahrtforschung, Vol.19, pp. 178, 1942.
• [9] Klunker, E. B., An analysis of supersonic aerodynamic heating with continuous fluid injection, N.A.C.A Tech. Note 1987, 1949.
• [10] Jubran, B., Brown, A., Film cooling from two rows of holes inclined to the stream wise and spanwise directions, Journal of Engineering for Gas Turbines and Power, No. 107, pp. 84-91, 1985.
• [11] Aly, S. E., Injection efect on two dimensional boundary layer, Journal of Energy Conversion & Management, No. 41, pp. 539-550, 2000.
• [12] Hargrove, W. J., The C-5A active lift distribution control system, NASA Technical Document, No. N76-31X48, 1976.
• [13] Chirayath, V., Alonso, J., Plasma actuated unmanned aerial vehicle – the first plasma controled flight in history, published by Standford University, 2011.
• [14] Stalewski, W., Sznajder, J., Modification of aerodynamic wing loads by fluidic devices, Journal of KONES Powertrain and Transport, Vol. 21, No. 3, pp. 271-278, 2014.
• [15] Stalewski, W., Sznajder, J., Computational simulations of smart aircraft-wing-load-control systems based on innovative fluidic devices, proceedings of Workshop on Applied Modelling and Simulation, WAMS, pp. 21-26, 2014.