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In the previous discussion, we investigated the static aeroelastic behaviour of straight (unswept) wings. These wings are characterised by an effective decoupling of wing bending and wing twist ruling out the influence of bending as a factor. Two critical dynamic pressures (or equivalently flight speeds) have been presented representing the torsional divergence and control surface reversal phenomena. A third important critical dynamic pressure is related to the dynamic aeroelastic instability of flutter, which will be discussed later on. For straight wings, the flutter dynamic pressure is most critical, while information of torsional divergence and control surface reversal phenomena are important to establish the overall aeroelastic picture of the aircraft.For swept wings, bending has an important and complicating impact on the aeroelastic stability characteristics. These will be presented qualitatively in the following.
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Calculating the thrust of the engine: When applying the above method to calculate the individual thrust loads on the various components it is assumed that the engine is static.
In the Aircraft Performance course, the aircraft was assumed to be in a steady-state (e.g. steady cruise, climb, turn, glide), with the forces and moments balanced. The subject of
Virtual prototyping techniques provide unique way of interacting with computer data and images. These removes the barriers of key board, monitor and mouse and allow user to experi
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FIRING ORDER If in multi cylinder engines, various cylinders are made to fire one after the other, interference between adjacent cylinders would occur, since these may have o
Air flow control system – operation: The stages of the compressor are matched to give the highest efficiency in the speed range maximum rev/min. To extend the range of smooth
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ADVANTAGES The small size of the IC is its most apparent advantage. A typical IC can be constructed on a piece of semiconductor material that is less than 4mm2. Even when the
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