Canard flow improvement in a split canard configuration

Abstract

Extensive low-speed wind-tunnel tests are performed to study the flow field structure over a dual-surface canard, known as split canard, in comparison to the conventional configurations. Surface pressure for both steady deflections and unsteady oscillations of the canard are measured and compared for both canard-alone and split-canard cases. The split canard shows a superior advantage at high angles of attack, where a delay in the vortex breakdown phenomena on the canard surface is observed. For the split-canard configuration, the downwash of the front canard reduces the effective angle of attack at the inboard section of the rear element which postpones formation of the leading-edge vortex. Furthermore, a region of considerably high suction was observed at front portion of the rear canard when compared with the isolated canard case. This can be thought of as the main mechanism of performance enhancement in split canards comparing to the conventional configurations.

Keywords

Canard delta wing downwash leading edge vortex

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References

Omar

Suresh

. Experimental investigation of incompressible flow around delta wing-slender body combinations. Int J Appl Eng Res (IJAER) 2007; 2: 685–698.

Su W-J and Wilson C. Aerodynamic characterization of a canard guided artillery projectile. AIAA Paper 2007-672, 45th AIAA Aerospace Sciences Meeting and Exhibit, 8–11 January 2007, Reno, Nevada.

Pandya SA and Aftofmis MJ. Computation of external aerodynamics for a canard rotor/wing aircraft. AIAA Paper 2001-0997, 39th Aerospace Sciences Meeting and Exhibit, 8–11 January 2001, Reno, Nevada.

Earnshaw PB and Lawford IA. Low-speed wind tunnel experiments on a series of sharp-edged delta wings. Aeronautical Research Council, Reports and Memoranda, No. 3424. London: HMSO, 1964.

Howard

O’Leary

. Flow field study of a close-coupled canard configuration. J Aircraft 1994; 31: 908–914.

Oelker HC and Hummel D. Investigations on the Vorticity Sheets of a Close-Coupled Delta-Canard Configuration. J Aircraft 1989; 26(7): 657–666.

. Vortex wing interactions of a close-coupled canard configuration. Journal of Aircraft 1994; 31(2): 314–324.

Ekaterinaris

. Analysis of flowfields over missile configurations at subsonic speeds. Journal of Spacecraft and Rockets 1995; 32(3): 385–391.

Tuncer IH and Platzer MF. A computational study of a close-coupled delta canard-wing-body configuration. AIAA Paper 96-2440-CP, 1996.

10.

Liu

Wen

Zhang

. Experimental study of canard-spanwise pulsed blowing on a canard configuration. Journal of Aircraft 2008; 45: 1816–1820.

11.

Cui

Lim

. and Tsai HM. Forebody slot blowing on vortex breakdown and load over a delta wing. AIAA J 2008; 46: 744–751.

12.

Chung HS, Seaver CA and McLaughlin TE. Vortex flow control over a delta wing by co-rotating and counter rotating vortex generator. In: 28th AIAA Applied Aerodynamics Conference, AIAA Paper 2010–4952, 28 June–1 July 2010, Chicago, Illinois.

13.

Fleeman

. Tactical missile design, USA: The American Institute of Aeronautics and Astronautics (AIAA), 2001.

14.

Lee

. Lift force of delta wings. Appl Mech Rev 1990; 43: 109–221.

15.

Hummel

Oelker

. Low-speed characteristics for the wing-canard configuration of the international vortex flow experiment. J Aircraft 1994; 31: 868–878.

16.

Katz

Davidovitch

Levint

. A split-canard configuration for improved control at high angles of attack. J Spacecraft and Rockets 1986; 23: 585–589.

17.

Honkanen T, Tuisku T and Pankkonen A. CFD simulations and wind tunnel experiments of a generic split-canard air-to-air missile at high angles of attack in turbulent subsonic flow. AIAA Paper 2011-6335 AIAA Atmospheric Flight Mechanics Conference, 8–11 August 2011, Portland, Oregon.

18.

Davari

Hadi Doolabi

Soltani

. Aspects of canard-wing vortices interaction in subsonic flow. Journal of Scientia 2012. manuscript submitted.

19.

Barlow

Rae

Jr Pope

. Low-speed wind tunnel testing, 3 rd ed. USA: John Wiley & Sons INC, 1999.

20.

Thomas

Roy

John

HLV

. Mechanical measurements, USA: Addison-Wesley Publishing Company, 1993.

21.

Malcom GN. Impact of high alpha aerodynamics on dynamic stability parameters of aircraft and missile. AGARD-LS-114, 1981. Proceedings of AGARD conference on Dynamic Stability Parameters, pp.2-1--2-21.

22.

Davari

Soltani

Attarian

. Surface pressure contour prediction using a GRNN algorithm. IJE Trans C: Aspects 2014; 27: 729–739.