By C. Abegg, H. Bippes, F. P. Bertolotti (auth.), Wolfgang Nitsche, Hans-Joachim Heinemann, Reinhard Hilbig (eds.)
This quantity comprises the papers of the eleventh Symposium of the AG STAB (German Aerospace Aerodynamics Association). during this organization these scientists and engineers from universities, research-establishments and are concerned, who're doing study and venture paintings in numerical and experimental fluid mechanics and aerodynamics for aerospace and different purposes. a number of the contributions are giving effects from the "Luftfahrtforschungsprogramm der Bundesregierung (German Aeronautical learn Programme). many of the papers document on paintings backed by way of the Deutsche Forschungsgemeinschaft, DFG, which additionally was once awarded on the symposium. the quantity supplies a extensive evaluation over the continuing paintings during this box in Germany.
Read or Download New Results in Numerical and Experimental Fluid Mechanics II: Contributions to the 11th AG STAB/DGLR Symposium Berlin, Germany 1998 PDF
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Extra info for New Results in Numerical and Experimental Fluid Mechanics II: Contributions to the 11th AG STAB/DGLR Symposium Berlin, Germany 1998
5 for the excitation frequency of 430 Hz. But, the hysteresis loop is much smaller in this case of lower excitation frequency. Fig. 4 shows, for three different angles of attack, the minimum sound pressure level A required to obtain attached flow as a function of the excitation frequency. In all cases the flow was separated under natural conditions. The slot was again at 5 % of the chord length. It is obvious that there are three frequency bands where only low sound pressure levels are necessary to obtain an attached flow.
NM. 33 174 Measuring Volume Mirror 1_40) i Front lens Beam Splmer ReceIVing lens Mirror 1_40) ReceMng Fiber Front Lens 1-120(6)<40) Beam Splitter Minor 16lofiX4O) I ~ 174 Fig. 1: Cross sectional view of LDA probe for in-flight measurements 34 Fig. 2: LOA system during in-flight tests Cockpit • On Board Computer • Keyboard • Display Flight Data Acquisition • Total Pressure • Static Pressure • • • • Temperature Air Humidity Pitch Angle Yaw Angle Instrumentation Platform UndBfWlng S1aUon Wlng Glove • Traversing Control • Excitation Source • Excitation Source Control • LOA Probe • Probe Traversing System • Nd-YAG-Laser • Photodetector • lOA Processor (BSA) Fig.
Points and with 400 points, respectively, Fig. 5 and Fig. 6. The Cp distortion is so small that it is visible in the shape factor plot only. The amplification rates using different stepsizes are shown in Fig. 7 and Fig. 8 (100 respectively 400 points in the mean flow direction). The gradient between two points (larger for the case with 400 mean flow points) of the stochastically disturbed mean flow has a larger influence on the amplification rates than the absolute deviation. This is proven by a PSE run with 400 mean flow points and aPSE stepsize which gives the same number of stations (streamwise) as a PSE run with 100 points and reduced PSE stepsize.
New Results in Numerical and Experimental Fluid Mechanics II: Contributions to the 11th AG STAB/DGLR Symposium Berlin, Germany 1998 by C. Abegg, H. Bippes, F. P. Bertolotti (auth.), Wolfgang Nitsche, Hans-Joachim Heinemann, Reinhard Hilbig (eds.)