Wind Tunnel Measurements of Hysteresis in the Static Aerodynamic Characteristics of Aircraft

Wind Tunnel Measurements of Hysteresis in the Static Aerodynamic Characteristics of Aircraft PDF Author: J. F. Herman
Publisher:
ISBN:
Category : Hysteresis
Languages : en
Pages : 112

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Wind Tunnel Measurements of Hysteresis in the Static Aerodynamic Characteristics of Aircraft

Wind Tunnel Measurements of Hysteresis in the Static Aerodynamic Characteristics of Aircraft PDF Author: J. F. Herman
Publisher:
ISBN:
Category : Hysteresis
Languages : en
Pages : 112

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Book Description


Wind Tunnel Measurements of Hysteresis in the Static Aerodynamic Characteristics of Aircraft

Wind Tunnel Measurements of Hysteresis in the Static Aerodynamic Characteristics of Aircraft PDF Author: J. F. Herman
Publisher:
ISBN:
Category : Hysteresis
Languages : en
Pages : 0

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Wind Tunnel Investigation of the Aerodynamic Hysteresis Phenomenon on the F-4 Aircraft and Its Effects on Aircraft Motion

Wind Tunnel Investigation of the Aerodynamic Hysteresis Phenomenon on the F-4 Aircraft and Its Effects on Aircraft Motion PDF Author: J. F. Herman
Publisher:
ISBN:
Category : Hysteresis
Languages : en
Pages : 98

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A wind tunnel test program and an analytical study were conducted to investigate aerodynamic hysteresis phenomena on the F-4 aircraft. The wind tunnel test was conducted in the Arnold Engineering Development Center (AEDC) Aerodynamic Wind Tunnel (4T) to investigate the source of aerodynamic hysteresis in static aerodynamic data. The wind tunnel test also provided data that were used in a motion simulation study of the effect of hysteresis on predicted aircraft motion. Static longitudinal lateral directional force and moment data and wing pressure data were obtained on a 0.5-scale model (without pylons or external stores) with various simulated leading-edge slats. These data include the effects of Mach number, angle of attack, model movement, and time dependence on the aerodynamic hysteresis characteristics. Data are presented for the Mach number range from 0.7 to 0.95 at angles of attack from -4 to 24 deg at zero deg sideslip angle and for sideslipe angles from -12 to 12 deg at angles of attack of 5, 10, 15, and 20 deg. Six-degrees-of-freedom motion simulation studies were used to assess the effect of hysteresis in the rolling-moment coefficient on the prediction of aircraft motion. Simulations of various flight maneuvers were conducted both with and without hysteresis in the aerodynamic data. (Author).

Wind Tunnel Test to Investigate Aerodynamic Hysteresis Phenomena of the F-4 and F-111 Aircraft Models

Wind Tunnel Test to Investigate Aerodynamic Hysteresis Phenomena of the F-4 and F-111 Aircraft Models PDF Author: Joseph F. Herman
Publisher:
ISBN:
Category :
Languages : en
Pages : 37

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Wind tunnel tests were conducted to investigate aerodynamic hysteresis phenomena found in other investigations of the F-4 and F-111 aircraft models. A 1/20-scale model of the F-4C aircraft was used to obtain static force, moment and wing pressure data in pitch and sideslip over a Mach number range from 0.7 to 0.95. A 1/24-scale model of the F-111 aircraft was used to obtain static force and moment data for a Mach number range of 0.7 to 1.3. Data on the F-111 were obtained for wing sweep angles of 26 and 54 deg. In addition, tuft and oil flow visualization data were obtained for selected configurations. (Author).

Technical Abstract Bulletin

Technical Abstract Bulletin PDF Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 992

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Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 332

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Hysteresis Effects on Wind Tunnel Measurements of a Two-element Airfoil

Hysteresis Effects on Wind Tunnel Measurements of a Two-element Airfoil PDF Author: Kasim Biber
Publisher:
ISBN:
Category :
Languages : en
Pages :

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On the Formulation of the Aerodynamic Characteristics in Aircraft Dynamics

On the Formulation of the Aerodynamic Characteristics in Aircraft Dynamics PDF Author: Murray Tobak
Publisher:
ISBN:
Category : Nonlinear functional analysis
Languages : en
Pages : 76

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Book Description
The theory of functionals is used to reformulate the notions of aerodynamic indicial functions and superposition. Integral forms for the aerodynamic response to arbitrary motions are derived that are free of dependence on a linearity assumption. Simplifications of the integral forms lead to practicable nonlinear generalizations of the linear superposition and the stability derivative formulations. Applied to arbitrary nonplanar motions, the generalization yields a form for the aerodynamic response that can be compounded of the contributions from a limited number of well-defined characteristic motions, in principle reproducible in the wind tunnel. Further generalizations that would enable the consideration of random fluctuations and multivalued aerodynamic responses are indicated.

Wind Tunnel Measurement of Static Stability and Control Characteristics of a Representative Supersonic Interceptor Airplane at Mach Numbers from 0.8 to 1.2

Wind Tunnel Measurement of Static Stability and Control Characteristics of a Representative Supersonic Interceptor Airplane at Mach Numbers from 0.8 to 1.2 PDF Author: Dana S. Morse
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 120

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Aeronautical Engineering

Aeronautical Engineering PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580

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Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)