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By W. F. Durand (auth.), William Frederick Durand (eds.)

ISBN-10: 3642896278

ISBN-13: 9783642896279

ISBN-10: 3642914845

ISBN-13: 9783642914843

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Extra info for Aerodynamic Theory: A General Review of Progress Under a Grant of the Guggenheim Fund for the Promotion of Aeronautics

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FJ. '2 \ ~ ... 1 for normal operation. (/0. 0. 8 118 V lying between that for nO. Fig. 2. best efficiency and that for zero thrust are values for small and decreasing values of thc slip and, for a given thrust, would require a prohibitive diameter of propeller. The range of practically operative values of v/nD lies normally near and below that for best efficiency and for this range there is, for the combination, a loss in net thrust. -- " " \' '-', Similarly as for the thrust, the torque and hence the shaft power coefficient for the combination is increased for large values of vjnD and decreased for small values, with a crossing point apparently at a smaller value of v/nD than for the thrust (see Fig.

It is known that the radius of curvature of an ellipse at the extremity of its major axis 2a is b21a and at the extremity of its minor axis 2b is a2lb. We have thus given or assumed, band r = b2la. We have then a = b2/r, the half length of the equivalent ellipsoid. Then the elongation ratio to be used in the computation of the inertia factors = alb = blr. Since the point of maximum pressure occurs on the meridian we consider the motion symmetrical about the meridian plane. The tangent at the point of greatest pressure is at right angles to maximum velocity W of the flow, and the tangent at the point of greatest suction is parallel to the same direction.

K, axial; 10, transverse; k' rotation. cular cross sections, it will be exact enough to take the factor k' of the equivalent ellipsoid. For other cases, this factor, then denoted by le', must be multiplied by'Yj, the inertia factor of the cross section, or by its average value over the length. 1) where 'Yj refers to the direction in which the cross sections are moving when rotating. 6. Nose Pressure. The knowledge of the pressure distribution near the bow of airships is of particular importance, especially for ships of the semi-rigid or non-rigid type, because the pressure there reaches its maximum and minimum values, and thus determines the rigidity and strength of the bow stiffening to be provided.

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Aerodynamic Theory: A General Review of Progress Under a Grant of the Guggenheim Fund for the Promotion of Aeronautics by W. F. Durand (auth.), William Frederick Durand (eds.)


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