Notes on the Stalling of Vertical Tail Surfaces and on Fin Design
Notes on the Stalling of Vertical Tail Surfaces and on Fin Design

Author: F. L. Thompson

Publisher:

Published: 1940

Total Pages: 566

ISBN-13:

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It may be concluded that the stalling of vertical tail surfaces is not in itself a dangerous condition. Provided sufficient directional stability exists at large angles of sideslip, the tail stall may occur with modern airplanes, as with those of the past, without the knowledge of or concern to the pilot.

The Theoretical Lateral Motions of an Automatically Controlled Airplane Subjected to a Yawing-moment Disturbance
The Theoretical Lateral Motions of an Automatically Controlled Airplane Subjected to a Yawing-moment Disturbance

Author: Frederick H. Imlay

Publisher:

Published: 1941

Total Pages: 546

ISBN-13:

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The lateral motion resulting from a disturbance of the type produced by asymmetric loss of thrust has been determined for a hypothetical average airplane equipped with an automatic pilot. Plots of the resultant motion and the various modes that constitute the motion are presented for controls fixed and for various amounts of automatic control. The automatic control is assumed to be of a type that produces aileron deflections proportional to the angle of bank and rudder deflections proportional to the angle of azimuth. The use of an automatic control may introduce either of two modes. The first mode is primarily a rolling oscillation; the second is a poorly damped long-period oscillation in azimuth and bank . The motion following any change in trim causes the airplane to reach a state of equilibrium on a different flight heading from that existing before the disturbance and the airplane assumes a new flight attitude.

Effect of Some Present-day Airplane Design Trends on Requirements for Lateral Stability
Effect of Some Present-day Airplane Design Trends on Requirements for Lateral Stability

Author: Millard J. Bamber

Publisher:

Published: 1941

Total Pages: 32

ISBN-13:

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The results of the computations are presented in the form of diagrams of variations of fin area with dihedral angle from neutral stability. The results indicate that ncreasing the values of wing loading and moments of inertia makes the attainment of lateral stability increasingly difficult and even doubtful in some cases for airplanes with flaps deflected. The fin area required for lateral stability is more dependent on fuselage size than on wing area.