By Tuncer Cebeci
The 3rd Symposium on Numerical and actual features of Aerodynamic Flows, like its instant predecessor, used to be geared up with emphasis at the calculation of flows proper to airplane, ships, and missiles. Fifty-five papers and 20 short communications have been provided on the Symposium, which was once held on the California country collage at lengthy seashore from 21 to 24 January 1985. A panel dialogue used to be chaired by means of A. M. O. Smith and includeq kingdom ments by means of T. T. Huang, C. E. lobe, l. Nielsen, and C. okay. Forester on priorities for destiny examine. the 1st lecture in reminiscence of Professor Keith Stewartson used to be added through J. T. Stuart and is reproduced during this quantity including a range of the papers provided on the Symposium. In quantity II of this sequence, papers have been chosen with the intention to offer a transparent indication of the diversity of approaches on hand to symbolize two-dimensional flows, their actual beginning, and their predictive skill. during this quantity, the emphasis is on 3-dimensional flows with a bit of 5 papers all in favour of unsteady flows and a bit of 7 papers on 3 dimensional flows: The papers deal quite often with calculation tools and surround subsonic and transonic, connected and separated flows. The selec tion has been made that allows you to satisfy an identical objective for three-d flows as did quantity II for two-dimensional flows.
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Extra resources for Numerical and Physical Aspects of Aerodynamic Flows III
11). BF represents the sum of these momentum thicknesses taken at the trailing edge. This quantity can be related to the drag coefficient by using the Squire-Young relation, but we must be very careful, since we have neglected the viscous-inviscid interaction. A discrepancy of 5% on the potential velocity at the trailing edge can induce a discrepancy of 15% on the drag coefficient. For (() = 0°, BF is practically constant as Rc increases to 40 million. In fact, there is competition between the decrease in and the slowly forward movement of transition due to the increase in Reynolds number.
As explained by Stuart , it is possible [in a problem for which A(t) is a function of t only] to maintain a constant pressure gradient (Pekeris and Shkoller) or to maintain a constant mass flux (Reynolds and Potter). ) In the case of time-growing perturbations the results of Reynolds and Potter and of Pekeris and Shkoller are qualitatively similar (Fig. 8). Within the dashed curve aIr < 0, but outside aIr> 0. Similar results were obtained by Hoh  for spatially growing ° disturbances. R Figure 8.
Transition due to streamwise instability (S) appears between 35 and 45% of the chord. For Rc less than 10 million, the boundary layer remains laminar up to the separation line (LS), due to the strong positive pressure gradients which exist on the rear part of the wing. Transition may occur within separation, but we cannot compute it with the present numerical model. Let us notice that, at a given Rc ' C-type transitions move downstream when (tn increases, though S-type transitions go upstream. Results concerning the lower side of the wing are presented in Fig.