Estimation of the Damping in Roll of Wings Through the Normal Flight Range of Lift Coefficient PDF Download
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Author: Alex Goodman Publisher: ISBN: Category : Aerofoils Languages : en Pages : 38
Book Description
The development of three methods for calculating the damping in roll through the normal flight range of lift coefficient for wing plan forms having various sweep angles, aspect ratios, and taper ratios is presented and comparisons between experimental and calculated results are made.
Author: Alex Goodman Publisher: ISBN: Category : Aerofoils Languages : en Pages : 38
Book Description
The development of three methods for calculating the damping in roll through the normal flight range of lift coefficient for wing plan forms having various sweep angles, aspect ratios, and taper ratios is presented and comparisons between experimental and calculated results are made.
Author: S. S. Manson Publisher: ISBN: Category : Aeronautics Languages : en Pages : 730
Book Description
A review is presented of available information on the behavior of brittle and ductile materials under conditions of thermal stress and thermal shock. For brittle materials, a simple formula relating physical properties to thermal-shock resistance are derived and used to determine the relative significance of two indices currently in use for rating materials. The importance of simulating operating conditions in thermal-shock testing is deduced from the formula and is experimentally illustrated by showing that BeO could be both inferior or superior to Al2O3 in thermal shock depending on the testing conditions. For ductile materials, thermal-shock resistance depends upon the complex interrelation among several metallurgical variables which seriously affect strength and ductility. These variables are briefly discussed and illustrated from literature sources. The importance of simulating operating conditions in tests for rating ductile materials is especially to be emphasized because of the importance of testing conditions in metallurgy. A number of practical methods that have been used to minimize the deleterious effects of thermal stress and thermal shock are outlined.
Author: James W. Wiggins Publisher: ISBN: Category : Airplanes Languages : en Pages : 56
Book Description
An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.
Author: James T. Matthews Publisher: ISBN: Category : Acceleration (Mechanics) Languages : en Pages : 726
Book Description
A theoretical analysis was made to investigate the performance and acceleration-restriction capabilities of a normal-acceleration command control system in a fighter airplane. Several combinations of pitching velocity and pitching acceleration were investigated as feedback quantities in combination with normal acceleration.
Author: Alex Goodman
Author: Alex Goodman
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: S. S. Manson
Author: James W. Wiggins
Author: James W. Wiggins
Author: James T. Matthews
Author: 
Author: James W. Wiggins