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Aerodynamics for Engineering Students by E. Houghton, P. Carpenter

By E. Houghton, P. Carpenter

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This force may be resolved into components SX and 6 2 in the x and z directions. 57) and from the geometry Basic concepts and definitions 39 Fig. g. the stagnation pressure in the free stream). 58) can readily be converted into coefficient form. 59b) where the contour integral is evaluated by following an anti-clockwise direction around the contour C of the aerofoil. Similar arguments lead to the following relations for X. 6Xu = pubs sin E, 6Xe = pe6s sin E : 6s sin E = 6z, giving where zmuand zme are respectively the maximum and minimum values of z, and AC, is the difference between the values of C, acting on the fore and rear points of an aerofoil for a fixed value of z.

Then and, assuming that this function (. 34) where each factor has been replaced by its dimensions. 3%) Here are three equations in four unknowns. One unknown must therefore be left undetermined:f, the index of u,is selected for this role and the equations are solved for a, b and e in terms off. 38) where g represents some function which, as it includes the undetermined constant C and index f, is unknown from the present analysis. 38) is extremely valuable, as it shows that the values of nd/V should depend only on the corresponding value of V d / v ,regardless of the actual values of the original variables.

The total drag of a body appears as a loss of momentum and increase of energy in this wake. The loss of momentum appears as a reduction of average flow speed, while the increase of energy is seen as violent eddying (or vorticity) in the wake. The size and intensity of the wake is therefore an indication of the profile drag of the body. 17 gives an indication of the comparative widths of the wakes behind a few bodies. 6 Estimation of the coefficients of lift, drag and pitching moment from the pressure distribution Let Fig.

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