Wind Tunnel Measurements of Hysteresis in the Static Aerodynamic Characteristics of Aircraft PDF Download
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Author: J. F. Herman
Publisher:
ISBN:
Category : Hysteresis
Languages : en
Pages : 112
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Book Description
Author: J. F. Herman
Publisher:
ISBN:
Category : Hysteresis
Languages : en
Pages : 112
Get Book Here
Book Description
Author: J. F. Herman
Publisher:
ISBN:
Category : Hysteresis
Languages : en
Pages : 98
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Book Description
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).
Author:
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ISBN:
Category : Science
Languages : en
Pages : 992
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Author:
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Category : Aeronautics
Languages : en
Pages : 332
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Author:
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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)
Author:
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Category : Government publications
Languages : en
Pages : 1020
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Author: John Stack
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 70
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The effects of scale and turbulence on the lift and drag of five airfoils, the N.A.C.A. 0006 , the N.A.C.A. 0021, the Clark Y, The U.S.A 35-A, and the U.S.N. P.S.6, hve been investigated in the Variable Density Wind Tunnel. Tests were made over a wide scale for only two different conditions of turbulence.
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Category : Power resources
Languages : en
Pages : 600
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Author: Murray Tobak
Publisher:
ISBN:
Category : Nonlinear functional analysis
Languages : en
Pages : 76
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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.
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Category : Government publications
Languages : en
Pages :
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