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AVLAB 1001-0150-009A DRIVER

The value of qm is a trade-off between computation time and accuracy and its selection is based on experience.

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Avlab 1001-0150-009A near wake technique results in about an order of magnitude reduction in computation time, which is a great improvement. There is a price for this reduction in computation time, and that is a major in- crease in the requirement for fast access memory capacity core storage. This may force the use of very large interval sizes or even prohibit the use of the near wake technique,depending on the computer available.

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The developments described above are primarily for the forward flight case. Hover is very different from forward flight because in hover there is no large uniform relative wind. This means that the wake does not spread out as rapidly and hence more of the wake must Avlab 1001-0150-009A considered when computing either airloads or Avlab 1001-0150-009A geometry. It also means that induced velocities are the only velocities present and therefore wake geometry is much more sensitive to changes in induced velocity.

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This increased sensi- tivity leads to instabilities in the tip vortex geometry as shown in [23,24]. Classical propeller theory [25,26] assumes no slipstream contraction.

This is adequate for axial flight,but not statically. One solution to this problem is to determine the slipstream con- traction envelope based on actuator disk Avlab 1001-0150-009A.

This envelope can be used directly in an actuator disk solution for airloads [27] or as the outer boundary of the vortex sheets trailed by each rotor blade [28]. To date these envelope solutions have not produced completely satisfactory results. Instead of the envelope approach, the distortion of the wake of each blade can be computed directly in a Avlab 1001-0150-009A similar to the forward flight wake geometry computation methods of [19, 22]. These methods [23,29,30] still do not accuately predict the tip vortex geometry near the rotor. In the far wake, the method of Avlab 1001-0150-009A predicts instability which agrees with experimental data [23,31].

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The method of [30] does Avlab 1001-0150-009A predict this insta- bility but instead computes an average location of the wake. This is due to computing induced velocities at fixed points in space rather than at points on the wake.

Since none of the theoretical methods of computing hover- ing rotor wake geometry is yet completely satisfactoryan em- pirical correlation method has been developed based on model test data [23,29,31,32]. This correlation method is currently the most Avlab 1001-0150-009A method of computing hovering rotor wake geometry. This Avlab 1001-0150-009A survey of previous investigations is intended to place the curren work in the context of previous and parallel efforts in this field.

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A more general survey of the literature can be found in 33]. It is, therefore, necessary to be able to compute tip vortex geometry as a part of an accurate vibratory airloads computation. Avlab 1001-0150-009A

Methods have been developed for computing tip vortex geometry, but they are very Avlab 1001-0150-009A. The current investigation therefore concentrates on developing inexpensive tip vortex geometry computation techniques with provisions for trading-off accuracy for cost.

In addition, an efficient air- loads computation is Avlab 1001-0150-009A, both to provide the circulation distribution as an input to the tip vortex geometry computation and to determine the effect of tip vortex geometry on harmonic airloads. The special case Avlab 1001-0150-009A hovering rotor tip vortex geometry is also studied.

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The wake is divided into three parts: Models are developed for each of these parts. These models are made up of straight vortex line segments, curved vortex line segments, and plane Avlab 1001-0150-009A vortex sheet segments.

These segments can either be of uniform circula- tion Avlab 1001-0150-009A or they can have a linear variation in circulation strength. The vortex line segments have a vortex core in which viscous effects become important. A basic wake model is developed. Download AVLAB Technology Windows Drivers Free.

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