By Peter Bradshaw (auth.), Dr. Werner Haase (eds.)
ISBN-10: 364281932X
ISBN-13: 9783642819322
ISBN-10: 3642819346
ISBN-13: 9783642819346
The current quantity entitled "Recent Contributions to Fluid Mechanics" is devoted to Professor Dr.-Ing. Alfred Walz in honour of his seventy fifth birthday. Alfred Walz, born on eleven may well 1907, started his impressive profession as an electric engineer. many years after acquiring his collage measure he grew to become tremendous engaged in fluid dynamics. jogging within the footsteps of Prandtl he was once capable of direct the advance of theoretical actions in an inimitable manner. He had the good chance to paintings either as an engaged fluid dynamicist -always attempting to resolve issues -and as a favored and sufferer instructor. To all of this stuff - in his personal phrases - he gave his center. for that reason, it's a nice excitement to put up the subsequent 34 contributions summarizing the efforts of fifty six authors. those artic les in overall hide the wide variety of experimental in addition to theore tical fluid dynamics and replicate the current cutting-edge. furthermore, all colleagues and neighbors of Alfred Walz want that he are able to proceed his paintings and his impression at the paintings of we all through his enlightening rules. Friedrichshafen, August 1982 Werner Haase Chairman of the clinical Committee desk of Contents SURVEY PAPER Shear Layer reports - previous, current, destiny P. Bradshaw .......................................... .
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F:---+---~20·0 28 26 24 x (in) 22 Fig. 7. Comparison of calculated results (solid line) with the experimental data (symbols) of East and Hoxey along z = 6". - - l Z=0 Z = 9" Fig. 8. Comparison between experimental and computed separation lines for the data of East and Hoxey. Note that the initial conditions at z = 9" were available for x up to 21". 38 10 22" CALCULATED o 0 EXPERIMENTAL DATA 26" 21" 24" 8 6 y (in) 4 2 °0L---~0----~0~~~0~~~~~~~~~~~~--~---C~--~ ut/u Se Fig. 9. Comparison of calculated velocity profiles with the experimental data of East and Hoxey along z • 6".
In this case a small loss of lift is measured in the corner region. As soon as rear separation takes place there is a distinct increase of lift near the reflection wall which influences the total lift coefficient remarkably. As the half model technique is often used in aerodynamic testing it seems to be worth-while to investigate in detail the features of secondary flows on the wing-reflection wall intersection. These secondary flows lead to errors in the symmetrical flow conditions which considerably exceed the displacement effect of the interferent boundary layers on the wing and the reflection wall.
This leads to a corxesponding increase of local lift (Fig. 4) whereas on the full model the local lift shows a minimum in the center plane. In order to diminish the error in the symmetrical flow conditions different attempts have been made. Those are boundary layer suction as well as partial and complete cover of the suction holes on the perforated wall section in order to prevent pressure compensation between the upper and lower sides of the wing. But the pressure distribution in the neighbouring measuring section could not be influenced (Fig.
Recent Contributions to Fluid Mechanics by Peter Bradshaw (auth.), Dr. Werner Haase (eds.)
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