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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.
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PROPELLER TORQUE Propeller torque is produced by the aerodynamic drag on the blades when in motion. Propeller torque acts in the plane of rotation and opposes engine torque.
Generally, there are three modes to describe different crack surface displacement in a cracked body. Mode I is opening or tensile mode where the crack surfaces move directly ap
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A tubular heat exchanger is being used for heating a liquid food from 30 o C to 70 o C. The temperature of the heating medium decreases from 90 o to 60 o C. a) Is the flow conf
Here, it is assumed that the crack is effectively longer than the value measured on the side of the specimen. If one assumes that it is longer by an amount Δ, then the new crack le
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