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The centre of pressure (CP) is defined as the point about which the resultant moment is zero; the net effect of the flow in terms of forces and moments would be the same as if the resultant force vector were located at the CP. The problem with using the CP in the analysis of aircraft stability and flight dynamics is that the CP is a function of incidence α and moves around considerably; indeed it is not always even within the aerofoil.
The flow-field around an aircraft results in a pressure distribution that in turn gives rise to a normal pressure force and a surface shear force distribution. Just as with any system of forces, these complex force distributions can be represented by a simple equivalent force system that provides: 1. An identical resultant force; 2. An identical moment. (Identical about any point.) Furthermore, the resultant aerodynamic force can be resolved into lift, drag, and (in asymmetric flight) side-force components; see Fig. 2.1-1. The flow also produces a resultant moment about any given point, e.g. ‘a' in Fig. 2.1-1. This is denoted Ma. The moment about a different point would or course be different.
Slipstream Effect. In passing through the propeller the air is accelerated and given a rotational velocity. The parts of the aircraft that are in the propeller slipstream wi
Fire risk assessment process: This is the main part of the FRA process. Here we consider the risk, measure it against what we consider acceptable and, if we consider that t
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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 a
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calculate the workdone by a system which contains 10kg of this gas expanding from 1m^3 at temperature of 293k, use the values a=15.7*10Nm^4, b=1.07*10^-2m^3 , R=0.278KJ/Kg-k.
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