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The calculation of flow fields by panel methods: a report on Euromech 75

Published online by Cambridge University Press:  11 April 2006

H. Körner
Affiliation:
Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V. (DFVLR), Braunschweig and Köln, Germany
E. H. Hirschel
Affiliation:
Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V. (DFVLR), Braunschweig and Köln, Germany

Abstract

Self-diffusion coefficients were determined experimentally for lateral dispersion of spherical and disk-like particles in linear shear flow of a slurry at very low Reynolds number. Using a concentric-cylinder Couette apparatus, recurrent observations were made of the lateral position of a particular radioactively labelled particle. The self-diffusion coefficient D was calculated by means of random-walk theory, using the ergodic hypothesis. Owing to great experimental difficulties, the calculated values of D are not of high accuracy, but are correct to within a factor of two. In the range 0 < ϕ < 0·2, D/a2ω increases from zero linearly with ϕ up to D/a2ω ≈ 0.02 (where ϕ = volumetric concentration of particles, a = particle radius, ω = mean shear rate of suspending fluid). In the range 0.2 < ϕ < 0.5, the trend of D/a2ω is not clear because of experimental scatter, but in this range D/a2ω ≈ 0·025 to within a factor of two. Within the experimental accuracy, spheres and disks have the same value of D/a2ω.

Type
Research Article
Copyright
© 1977 Cambridge University Press

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References

Ahmed, S. R. Recent experiences in using panel methods for the calculation of subsonic flows at DFVLR Braunschweig.
Botta, E. F. F. Computation of potential flow around bodies using approximation by splines.
Coulmy, G. An extension of the discrete distribution of singularities method for the computation of the velocity field with non-zero divergence or curl.
Falkner, V. M. 1943 The calculation of the aerodynamic loading on surfaces of any shape. Aero. Res. Counc. R. & M. no. 1910.Google Scholar
Fray, J. M. J. A source lattice method for wing-thickness design.
Giesing, J. P. 1968 Lifting surface theory for wing–fuselage combinations. McDonnel-Douglas Rep. DAC 67212, vol. I.Google Scholar
Gustavsson, A. L. & Hedman, S. G. An improved version of a panel method for the prediction of aerodynamic characteristics of wing–body–tail combinations at subsonic and supersonic speeds.
Hedman, S. G. 1966 Vortex lattice method for calculation of quasi-steady state loadings on thin elastic wings in subsonic flow. Flugtekniska Försöksanstalten Rep. no. 105.Google Scholar
Hess, J. L. Survey of first-order panel methods.
Hummes, D. & Langer, J. H. A vortex theory to calculate rotor–wing interference.
Hunt, B. Economic improvements to the mathematical model in a plane/constant strength panel method.
Jepps, S. A. Tracking a free vortex.
Körner, H. 1972 Berechnung der potentialtheoretischen Strömung um Flügel-Rumpf-Kombinationen und Vergleich mit Messungen. Z. Flugwiss. 20, 351368.Google Scholar
Kraus, W. State of theory and application of panel methods at MBB.
Lind, I. A. Wind-tunnel interference effects between swept wings and tunnel walls studied by a VLM-method.
Lock, R. C. Comparison of panel methods. (Combined Boeing, BAC and NLR paper.)
Losito, V. & Napolitano, L. G. Calculation of flow fields by source–panel methods.
Lotz, I. 1931 Zur Berechnung der Potentialströmung um quergestellte Luftschiffkörper. Ing.-Arch. 2, 507527.Google Scholar
Lucchi, C. W. State of art in the vortex-lattice method for total force prediction.
Maczynski, J. A field superposition method for slow flows.
Mai, H. U. A vortex panel method for slowly oscillating lifting surface at subsonic speeds.
Martensen, E. 1959 Die Berechnung der Druckverteilung an dicken Gitterprofilen mit Hilfe der Fredholmschen Integralgleichungen zweiter Art. Arch. Rat. Mech. Anal. 3, 235270.Google Scholar
Maskew, B. A subvortex technique for the close approach to a discretized vortex sheet.
Oswatitsch, J. 1950 Die Geschwindigkeitsverteilung bei lokalen Überschallgebieten an flachen Profilen. Z. angew. Math. Mech. 30, 1724.Google Scholar
Prager, W. 1928 Die Druckverteilung an Körpern in ebener Potentialströmung. Phys. Z. 29, 865869.Google Scholar
Renken, J. & Starken, H. Calculation of three-dimensional cascade flow by means of a first-order panel method.
Roberts, A. Higher-order panel-type methods – the spline–Neumann system.
Roberts, A. & Rundle, K. 1972 Computation of incompressible flow about bodies and thick wings using the spline mode system. B.A.C. Aero. M. no. 19.Google Scholar
Roos, R. Application of panel methods for unsteady subsonic flow.
Rubbert, P. E. 1962 Theoretical characteristics of arbitrary wings by non-planar-vortex lattice method. Boeing Co. Rep. D6-9244.Google Scholar
Rubbert, P. E., Johnson, F. T., Brune, G. W. & Weber, J. A. Application of a higher-order subsonic panel method to configurations with free vortex flow.
Schmidt, W. AIC-methods for sub- and supersonic potential flow – a critical survey.
Schmitt, H. Pressure distribution at a plane wall caused by a round jet exhausting normally from the wall into a uniform cross-flow.
Sells, C. C. L. Iterative calculation of subcritical flow around thick cambered wings – direct and design problems.
Smith, A. M. O. & Hess, J. L. 1967 Calculation of potential flow about arbitrary bodies. Prog. Aero. Sci. 8, 1138.Google Scholar
Sockel, H. 1971a Linearisierung der instationären, gasdynamischen Gleichung und Diskussion der Voraussetzungen an verschiedenen Fällen. Z. angew. Math. Mech. 51, 299302.Google Scholar
Sockel, H. 1971b Singuläre Lösungen der instationären, linearisierten, gasdynamischen Gleichung. Z. angew. Math. Mech. 51, 371376.Google Scholar
Steinheuer, J. A study on the passing of two trains treated as a two-dimensional quasi-steady problem.
Stricker, R. On an ‘influence-coefficient-method’ for calculation of the fully nonlinear stationary subsonic potential flow about arbitrary section shapes.
Struck, H. & Klevenhusen, K.-D. The prediction of jet interference effects by means of panel methods.
Vandrey, F. 1937 Zur theoretischen Behandlung des gegenseitigen Einflusses von Tragfläche und Rumpf. Luftfahrtforsch. 14, 347355.Google Scholar
Weakley, G. M. The application of panel methods in calculating wing/pod interference effects.
Woodward, F. A. 1968 Analysis and design of wing–body combinations at subsonic and supersonic speeds. J. Aircraft, 5, 528534.Google Scholar