By D. Reckzeh (auth.), Prof. Dr.-Ing. Siegfried Wagner, Dr.-Ing. Ulrich Rist, Dr.-Ing. Hans-Joachim Heinemann, Dipl.-Ing. Reinhard Hilbig (eds.)
This quantity comprises the papers of the 12. Symposium of the STAB (German Aerospace Aerodynamics Association). during this organization, german scientists and engineers from universities, research-establishments and are concerned, who're doing study and undertaking paintings in numerical and experimental fluidmechanics and aerodynamics for aerospace and different functions. a few of the contributions supply effects from the "Luftfahrt- forschungsprogram der Bundesregierung (German Aeronautical examine Program)". a few of the papers record on paintings subsidized by means of the Deutsche Forschungsgemeinschaft, DFG, who have been additionally current on the symposium. This quantity provides a large assessment of the continuing paintings during this box in Germany.
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Additional resources for New Results in Numerical and Experimental Fluid Mechanics III: Contributions to the 12th STAB/DGLR Symposium Stuttgart, Germany 2000
Example text
In figure 10 the press ure distributions on the elements of the high-lift configuration at 46% half span are shown. On the slat there is a good agreement in the pressure distribution of the computation and the experiments except for the suction peak in the computation which is higher than the suction peak in the experiments. A similar behavior is found for the main wing. The computation almost lies on the experiment, only the double suction peaks are higher than experimental ones. This double peak is determined by variation in the curvature on the surface in a small area where the retracted slat ends.
This slat end vortex provokes two opposed effects in the flow field: First, it shields the wing root region against the down-wash of the sUITounding flow field and so enlarged the trend of flow separation in this area. And second, this negative effect is compensated by the induced rotating flow, which adds a flow component towards the root corner and thus induces higher-energy air into the root area. In the calculation on grid 11 the slat end vortex seems to burst after a short distance (fig. 13).
O. SMITH: "High-Lift Aerodynamics". 10 6 experiment 0 " calculation experiment ~ E Ü 4 Pos. 7 4 Pos. 106 Re=9·106 calculation ~ ----------. 1 L J ~ 4 7 Pos. ~ E Ü ~ J 4 5 Pos. 1 Pos. 5 ---B---- Pos. 7 ~ Pos. 5 ---B---- Pos. 88Mio. 15 Figure 7 Differences of the suction peak at the main airfoil element in dependency of the slat position of the H8Y configuration for Re = 9M io. l Pos. 5 ----e-- Pos. 7 ~ ~ ----A- ----A- experiment ~cp= POS. 1 Pos. 5 ----e-- POS. 7 calculation 2 ~cp calculation =2 Cl.