Author: Joseph F. Herman
Publisher:
ISBN:
Category :
Languages : en
Pages : 37
Book Description
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).
Wind Tunnel Test to Investigate Aerodynamic Hysteresis Phenomena of the F-4 and F-111 Aircraft Models
Author: Joseph F. Herman
Publisher:
ISBN:
Category :
Languages : en
Pages : 37
Book Description
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).
Publisher:
ISBN:
Category :
Languages : en
Pages : 37
Book Description
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).
Wind Tunnel Investigation of the Aerodynamic Hysteresis Phenomenon on the F-4 Aircraft and Its Effects on Aircraft Motion
Author: J. F. Herman
Publisher:
ISBN:
Category : Hysteresis
Languages : en
Pages : 98
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).
Publisher:
ISBN:
Category : Hysteresis
Languages : en
Pages : 98
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).
Wind Tunnel Measurements of Hysteresis in the Static Aerodynamic Characteristics of Aircraft
Author: J. F. Herman
Publisher:
ISBN:
Category : Hysteresis
Languages : en
Pages : 112
Book Description
Publisher:
ISBN:
Category : Hysteresis
Languages : en
Pages : 112
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1370
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1370
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
NASA Technical Memorandum
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 388
Book Description
Technical Abstract Bulletin
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 204
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 204
Book Description
NASA SP.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 624
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 624
Book Description
U.S. and U.S.S.R. Military Aircraft and Missile Aerodynamics (1970-1980)
Author:
Publisher:
ISBN:
Category : Aeronautics, Military
Languages : en
Pages : 76
Book Description
Publisher:
ISBN:
Category : Aeronautics, Military
Languages : en
Pages : 76
Book Description
A Wind Tunnel Test to Study the Mutual Interference of Multiple Bodies in the Flow Field of the F-4C Aircraft in the Transonic Speed Range
Author: A. A. Hesketh
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 176
Book Description
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 176
Book Description
Aeronautical Engineering
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 454
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).
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 454
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).