Lift-curve Slopes Determined in Flight on a Flexible Swept-wing Jet Bomber PDF Download
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Author: William S. Aiken (Jr.) Publisher: ISBN: Category : Acceleration (Mechanics) Languages : en Pages : 54
Book Description
An analysis is made of the effects of Mach number and dynamic pressure on the lift-curve slope of a large flexible swept-wing jet-propelled airplane by using flight measurements of normal acceleration and angle of attack with auxiliary instrumentation as needed. The methods and procedures used to correct the flight measurements (obtained in abrupt push-pull maneuvers) and to convert the flight test data to equivalent rigid conditions for comparison with rigid-model wind-tunnel tests are described in detail. The airplane angle of zero lift and the airplane-less-tail angle of zero lift for the Mach number range of the flight tests (0.42 to 0.81) are also presented. Excellent agreement was obtained in the comparison between flight and wind-tunnel rigid lift-curve slopes and angles of zero lift.
Author: William S. Aiken (Jr.) Publisher: ISBN: Category : Acceleration (Mechanics) Languages : en Pages : 54
Book Description
An analysis is made of the effects of Mach number and dynamic pressure on the lift-curve slope of a large flexible swept-wing jet-propelled airplane by using flight measurements of normal acceleration and angle of attack with auxiliary instrumentation as needed. The methods and procedures used to correct the flight measurements (obtained in abrupt push-pull maneuvers) and to convert the flight test data to equivalent rigid conditions for comparison with rigid-model wind-tunnel tests are described in detail. The airplane angle of zero lift and the airplane-less-tail angle of zero lift for the Mach number range of the flight tests (0.42 to 0.81) are also presented. Excellent agreement was obtained in the comparison between flight and wind-tunnel rigid lift-curve slopes and angles of zero lift.
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: North Atlantic Treaty Organization. Advisory Group for Aeronautical Research and Development. Structures and Materials Panel Publisher: ISBN: Category : Aeroelasticity Languages : en Pages : 308
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Structures and Materials Panel Publisher: ISBN: Category : Aeroelasticity Languages : en Pages : 306
Author: William S. Aiken (Jr.)
Author: William S. Aiken (Jr.)
Author: William S. Aiken (Jr.)
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: North Atlantic Treaty Organization. Advisory Group for Aeronautical Research and Development. Structures and Materials Panel
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Structures and Materials Panel
Author: United States. National Advisory Committee for Aeronautics