Horizontal-tail Parameters as Determined from Flight-test Tail Loads on a Flexible Swept-wing Jet Bomber PDF Download
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Author: William S. Aiken (Jr.) Publisher: ISBN: Category : Airplanes Languages : en Pages : 42
Book Description
An analysis is made of horizontal-tail loads on a flexible multiple-ending jet-propelled swept-wing medium bomber to determine the following horizontal-tail parameters: tail lift-curve slope due to tail angle of attack, tail lift-curve slope due to elevator deflection, tail pitching-moment coefficient due to elevator deflection, downwash factor and the elevator effectiveness factor; and to determine the centers of pressure loads due to angles of attack and elevator deflection. Comparison of the flight-determined parameters with the available low-speed wind-tunnel data indicated excellent agreement, and the locations of the centers of pressure of the loads were in reasonable agreement with predictions. Least-squares curve-fitting procedures are used throughout the analysis, and a method is developed for determining zero shifts for the strain-gage-measured horizontal-tail loads.
Author: William S. Aiken (Jr.) Publisher: ISBN: Category : Airplanes Languages : en Pages : 42
Book Description
An analysis is made of horizontal-tail loads on a flexible multiple-ending jet-propelled swept-wing medium bomber to determine the following horizontal-tail parameters: tail lift-curve slope due to tail angle of attack, tail lift-curve slope due to elevator deflection, tail pitching-moment coefficient due to elevator deflection, downwash factor and the elevator effectiveness factor; and to determine the centers of pressure loads due to angles of attack and elevator deflection. Comparison of the flight-determined parameters with the available low-speed wind-tunnel data indicated excellent agreement, and the locations of the centers of pressure of the loads were in reasonable agreement with predictions. Least-squares curve-fitting procedures are used throughout the analysis, and a method is developed for determining zero shifts for the strain-gage-measured horizontal-tail loads.
Author: Alton P. Mayo Publisher: ISBN: Category : Bending Languages : en Pages : 632
Book Description
A matrix solution for the spanwise bending moments and deflections of a torsionally rigid rotor blade subjected to an arbitrary loading is presented. The method includes the cantilever, teetering, and hinged blades in hovering and in steady forward flight. The method is comparatively short, involves only standard matrix procedures, and does not require that the mode shapes or natural frequencies be known.
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: William S. Aiken (Jr.)
Author: William S. Aiken (Jr.)
Author: William A. McGowan
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: Alton P. Mayo
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: James T. Matthews
Author: