Author: David F. Fisher
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
Surface Flow Visualization of Separated Flows on the Forebody of an F-18 Aircraft and Wind-tunnel Model
Wind Tunnel Investigation of Vortex Flows on F/A-18 Configuration at Subsonic Through Transonic Speeds
Author: Gary E. Erickson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 172
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 172
Book Description
Summary of In-flight Flow Visualization Obtained from the NASA High Alpha Research Vehicle
NASA Technical Memorandum
Scientific and Technical Aerospace Reports
NASA Technical Paper
In-flight Wing Pressure Distributions for the NASA F/A-18A High Alpha Research Vehicle
Author: Mark C. Davis
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 68
Book Description
Pressure distributions on the wings of the F/A-18A High Alpha Research Vehicle (HARV) were obtained using both flush-mounted pressure orifices and surface-mounted pressure tubing. During quasi-stabilized 1-g flight, data were gathered at ranges for angle of attack from 5 to 70 degrees, for angle of sideslip from -12 to +12 degrees, and for Mach from 0.23 to 0.64, at various engine settings, and with and without the leading edge extension fence installed. Angle of attack strongly influenced the wing pressure distribution, as demonstrated by a distinct flow separation pattern that occurred between the range from 15 to 30 degrees. Influence was seen on the outboard portion of the wing. Angle-of-sideslip influence on wing pressure distribution was strongest at low angle of attack. Influence of Mach number was observed in the regions of local supersonic flow, diminshing as angle of attack was increased. Engine throttle setting had little influence on the wing pressure distribution.
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 68
Book Description
Pressure distributions on the wings of the F/A-18A High Alpha Research Vehicle (HARV) were obtained using both flush-mounted pressure orifices and surface-mounted pressure tubing. During quasi-stabilized 1-g flight, data were gathered at ranges for angle of attack from 5 to 70 degrees, for angle of sideslip from -12 to +12 degrees, and for Mach from 0.23 to 0.64, at various engine settings, and with and without the leading edge extension fence installed. Angle of attack strongly influenced the wing pressure distribution, as demonstrated by a distinct flow separation pattern that occurred between the range from 15 to 30 degrees. Influence was seen on the outboard portion of the wing. Angle-of-sideslip influence on wing pressure distribution was strongest at low angle of attack. Influence of Mach number was observed in the regions of local supersonic flow, diminshing as angle of attack was increased. Engine throttle setting had little influence on the wing pressure distribution.
Monthly Catalogue, United States Public Documents
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1690
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1690
Book Description
Monthly Catalog of United States Government Publications
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 974
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 974
Book Description