Surface Flow Visualization of Separated Flows on the Forebody of an F-18 Aircraft and Wind-tunnel Model

Surface Flow Visualization of Separated Flows on the Forebody of an F-18 Aircraft and Wind-tunnel Model PDF Author: David F. Fisher
Publisher:
ISBN:
Category :
Languages : en
Pages : 24

Book Description


Wind Tunnel Investigation of Vortex Flows on F/A-18 Configuration at Subsonic Through Transonic Speeds

Wind Tunnel Investigation of Vortex Flows on F/A-18 Configuration at Subsonic Through Transonic Speeds PDF Author: Gary E. Erickson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 172

Book Description


Summary of In-flight Flow Visualization Obtained from the NASA High Alpha Research Vehicle

Summary of In-flight Flow Visualization Obtained from the NASA High Alpha Research Vehicle PDF Author: David F. Fisher
Publisher:
ISBN:
Category :
Languages : en
Pages : 44

Book Description


NASA Technical Memorandum

NASA Technical Memorandum PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 496

Book Description


Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704

Book Description


NASA Technical Paper

NASA Technical Paper PDF Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 174

Book Description


In-flight Wing Pressure Distributions for the NASA F/A-18A High Alpha Research Vehicle

In-flight Wing Pressure Distributions for the NASA F/A-18A High Alpha Research Vehicle PDF 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.

Monthly Catalogue, United States Public Documents

Monthly Catalogue, United States Public Documents PDF Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1690

Book Description


Monthly Catalog of United States Government Publications

Monthly Catalog of United States Government Publications PDF Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 974

Book Description


Wind Tunnel Investigation of Vortex Flows on F/A-18 Configuration at Subsonic Through Transonic Speed

Wind Tunnel Investigation of Vortex Flows on F/A-18 Configuration at Subsonic Through Transonic Speed PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 172

Book Description