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Measurement of flow-induced pressures on the surface of a model in a flow visualization water tunnel

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Abstract

Flow-induced pressures were measured on the surface of a delta wing in a flow visualization water tunnel, and at the same time the vortical flow over the wing was visualized using dye. For a free-stream velocity of 0.1 m/s used in the experiments, the pressures were small (less than 15 Pa). This is believed to be the first time that flow-induced pressures have been measured in a water tunnel at such a low velocity. Measured pressure distributions can now be properly interpreted in terms of observed detailed flow patterns, without having to undertake complementary wind tunnel experiments to measure model loading.

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Notes

  1. All pressure coefficients presented in this paper have negative values. For discussion purposes, a pressure coefficient having a value of −2.0 (for example) is considered to be a smaller pressure coefficient than one having a value of −3.0.

Abbreviations

c :

centreline chord of the delta wing (c=300.0 mm)

C p :

pressure coefficient on the surface of the delta wing

f :

frequency (Hz)

p ref :

static pressure measured by the reference static-pressure probe (Pa)

P ref :

total pressure measured by the reference total-pressure probe (Pa)

p wing :

flow-induced pressure at a pressure tapping on the delta wing (Pa)

R :

Reynolds number for the delta wing in water (R=Uc/v w)

s :

local semi-span of the delta wing (mm)

U :

free-stream velocity in the test section of the water tunnel (m/s)

x :

chordwise distance from the apex of the delta wing (mm)

y :

spanwise distance from the centreline chord of the delta wing (mm)

α :

angle of attack of the delta wing (deg)

β :

angle of sideslip of the delta wing (deg)

v w :

kinematic viscosity of water (m2/s)

ρ a :

density of air (kg/m3)

ρ w :

density of water (kg/m3)

References

  • Atashbaz G, Ahmed NA (1997) Asymmetry of vortex flow over slender delta wings. International aerospace congress 97, Sydney, Australia, 24–27 February 1997, pp 41–52

  • Erm LP (2000) An investigation into the feasibility of measuring flow-induced pressures on the surface of a model in the AMRL water tunnel. DSTO technical note 0323, Aeronautical and Maritime Research Laboratory, Melbourne, Australia

  • Fink PT, Taylor J (1967) Some early experiments on vortex separation. 2. Some low speed experiments with 20° delta wings. Aero Res Counc R&M 3489

  • Hummel D (1978) On the vortex formation over a slender wing at large angles of incidence. AGARD conference proceedings 247, High angle of attack aerodynamics, Sandefjord, Norway, 4–6 October 1978

  • Kegelman JT, Roos FW (1989) Effects of leading-edge shape and vortex burst on the flowfield of a 70-degree-sweep delta wing. AIAA 89-0086, presented at the 27th AIAA aerospace sciences meeting, Reno, NV, USA, 9–12 January 1989, pp 1–10

  • Lambourne NC, Bryer DW (1962) The bursting of leading-edge vortices—some observations and discussion of the phenomenon. Aero Res Counc R&M 3282

  • McKernan JF (1983) An investigation of the breakdown of the leading edge vortices on a delta wing at high angles of attack. Dissertation, Department of Aerospace and Mechanical Engineering, University of Notre Dame, Notre Dame, IN

  • Menke M, Yang H, Gursul I (1999) Experiments on the unsteady nature of vortex breakdown over delta wings. Exp Fluids 27:262–272

    Article  Google Scholar 

  • Roos FW, Kegelman JT (1990) An experimental investigation of sweep-angle influence on delta-wing flows. AIAA 90-0383, presented at the 28th AIAA aerospace sciences meeting, Reno, NV, USA, 8–11 January 1990, pp 1–10

  • Suárez CJ, Ayers BF, Malcolm GN (1994a) Force and moment measurements in a flow visualization water tunnel. AIAA 94-0673, presented at the 32nd Aerospace sciences meeting & exhibit, Reno, NV, USA, 10–13 January 1994, pp 1–12

  • Suárez CJ, Malcolm GN, Kramer BR, Smith BC, Ayers BF (1994b) Development of a multicomponent force and moment balance for water tunnel applications, vol 1 and 2. NASA contractor report 4642

  • Suárez CJ, Malcolm GN (1994) Water tunnel force and moment measurements on an F/A-18. AIAA 94-1802-CP, presented at the AIAA applied aerodynamics conference, Colorado Springs, CO, USA, 20–22 June 1994, pp 12–24

  • Suárez CJ, Malcolm GN (1995) Dynamic water tunnel tests for flow visualization and force/moment measurements on maneuvering aircraft. AIAA 95-1843-CP, presented at the 13th AIAA applied aerodynamics conference, San Diego, CA, USA, 19–22 June 1995, pp 658–670

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Acknowledgements

The author is grateful for help received from Dr. David Thompson, Head Aerodynamics Applications, from Mr. Ian Amott and Mr. Dennis Carnell, who assisted with the experiments, and from Mr. Owen Holland, who developed the data-acquisition software.

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  1. Aeronautical and Maritime Research Laboratory, PO Box 4331, 3001, Melbourne, Victoria, Australia

    L. P. Erm

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Erm, L.P. Measurement of flow-induced pressures on the surface of a model in a flow visualization water tunnel. Exp Fluids 35, 533–540 (2003). https://doi.org/10.1007/s00348-003-0667-0

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  • DOI: https://doi.org/10.1007/s00348-003-0667-0

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