The Theory and Practice of Aeroplane Design |
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aerofoil aeronautical aeroplane airscrew angle of incidence Angle of Pitch aspect ratio axis bending bending moment biplane blade Bleriot body resistance Bristol Fighter camber centre of pressure Chapter chassis chord component compression considerable considered curve density determined direction distance drag bracing effect efficiency elevator engine equation factor of safety feet flight Formula front fuselage horizontal horse-power increase inertia L/D ratio lateral force leading edge lift coefficient lift forces load longerons lower plane machine method moment of inertia moments monoplane necessary normal force obtained oscillation pitching moment plate position practice reactions rotation rudder shown in Fig skid slip stream span speed stability steel streamline stress diagram struts surface TABLE tail plane tests top plane triplane tube variation velocity vertical weight whence wind wing section wing structure Yawing zero ΙΟ
Δημοφιλή αποσπάσματα
Σελίδα 26 - If three forces, acting at a point, be represented in magnitude and direction by the sides of a triangle taken in order they will be in equilibrium.
Σελίδα 422 - Soon shall thy arm, unconquered steam, afar Drag the slow barge, or drive the rapid car ; Or on wide waving wings expanded bear The flying chariot through the fields of air...
Σελίδα 26 - If three forces acting at a point be in equilibrium they can be represented in magnitude and direction by the sides of any triangle which is drawn so as to have its sides respectively parallel to the directions of the forces.
Σελίδα 400 - Firstly, the air speed and engine revolutions are noted flying level at full throttle every 2,000 feet approximately by aneroid. From the aneroid reading and temperature observation at each height the density is obtained. The reading of the air speed indicator is then first corrected for instrumental errors by adding or subtracting the correction found by calibration tests over the cameras or speed course.
Σελίδα 371 - NPL, and it was found that the results were in good agreement with those calculated.
Σελίδα 125 - This condition is satisfied by a sine or cosine function of the form y = a sin (bx + c) ............ 2 where a, b, and c are constants to be determined by the conditions of the case.
Σελίδα 405 - That is to say, when the airplane is flying in steady level flight the lift on the wings is equal to the weight of the airplane.
Σελίδα 329 - ... in which the first factor represents a very short oscillation, which in most aeroplanes rapidly dies out and is of no importance. The second factor represents a relatively long oscillation involving an undulatory flight path with changes in pitch, forward speed, and altitude. The long oscillations should diminish in amplitude with time, in which case the motion is stable and the aeroplane will return to its original normal flight attitude if temporarily deviated therefrom by accidental cause....
Σελίδα 137 - Usually each monoplane wing has two parallel or slightly converging spars — the front and the rear spar. Each pair of spars, together with some central pylon or the landing chassis, taken as king post, form the front and the rear lift-trusses. Both are fixed in case of aileron control, or the front-truss is fixed and the rear one movable in case of warping. A monoplane has usually a double lift-trussing; the spars are at the same time members of both the lift and drift-trusses. Fig. 26...
Σελίδα 137 - Until now we have considered only the airplane wing-truss as viewed from the front, or the so-called lift-truss. Inside the wings, however, are placed the so-called drift-trusses.* Both the lift and the drift-trusses are combined to form a rigid three-dimension structure by means of bracing in planes passing through the struts and parallel to the plane of symmetry of the whole machine. This bracing is visible in the side-view of the airplane and I will call it side-bracing.