By A.S. Ginevsky, A. I. Zhelannikov
The ebook provides tools of mathematical modeling of vortex wakes of plane in flights at excessive altitudes and shut to the floor at take-off-landing regimes. The modeling relies on an in depth software of the strategy of discrete vortices in plane flights at excessive altitudes and on a conjugation of this technique with the imperative approach to predicting the turbulent boundary layer that is produced on the secondary wall transversal circulate caused via the plane vertex approach at take-of-landing regimes. during this latter case an interplay among the vortex wake of airplane and the secondary vortices generated at boundary layer separations is taken into account.
The authors think about individually equipment of modeling the close to and much vortex wakes of aircrafts with turbojets and air propellers they usually current the result of predicting vortex wakes of a chain of family and overseas aircrafts. The impression of variety of components is considered in those situations: turbulence and surroundings stratification, presence of part wind at take- off-landing regimes.
The computing device time intake whereas modeling the vortex wakes in response to the proposed strategy is three - four orders below in terms of utilizing the well known numerical methods.
The non-linear non-stationary mathematical version of sunshine plane circulation after they input the vortex wake of a heavy plane with an outline of attainable catastrophic results for the sunshine airplane is taken into account individually. A comparability among the prediction info and the experimental effects is given.
The ebook is meant for researchers and engineers, in addition to for academics, post-graduate and undergraduate scholars.
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Additional info for Vortex wakes of Aircrafts
Sample text
In the course of investigations into the characteristics of the far trailing wake behind aircraft, it was found that the wakes have many common features. It turned out that if certain conditions are met, it is possible to provide flow similarity in different far trailing wakes. Let us identify the corresponding similarity criteria. Consider the process of the formation of the vortex wake behind a thin rectangular wing of moderate aspect ratio. Assume that the flow past the wing’s leading edge is smooth and attached.
With that, the circular core is replaced by the central linear vortex and two concentric layers consisting of 6 and 12 vortices identical with the central one. The indicated vortex tubes induce a near-wall crossflow accompanied at high Reynolds numbers by the formation of a turbulent boundary layer. The Reynolds number is defined by the formula Re = V0 H0 /ν , where Vo is the velocity induced by one of the vortex tubes at the centerline of the other at the initial instant of time. When this layer separates in the region of positive pressure gradient, transverse vortices are generated with circulation of opposite sign.
Golovnev) for the MiG-29 fighter aircraft. Fig. 1. Plate-element representation of the MiG-29 fighter aircraft. The solid-element representation considers all components of an aircraft (fuselage, engine nacelles, wing, stabilizer, fin) as a combination of solid elements. This is the most complicated representation, but it practically always gives good results, especially in predicting the motion of aircraft. Presently, the most popular aircraft representation is the hybrid one. S. I. 1007/978-3-642-01760-5_3, © Springer-Verlag Berlin Heidelberg 2009 34 Ch.
