Add to ORKGA configuration concept for developing vortex lift, which replaces the physical wing strake with a jet sheet generated fluid strake, was investigated on a general research fighter model. The vertical and horizontal location of the jet sheet with respect to the wing leading edge was studied over a momentum coefficient range from 0 to 0.24 in the Langley 7- by 10-foot high speed tunnel over a Mach number range from 0.3 to 0.8. The angle of attack range studied was from -2 to 30 deg at sideslip angles of 0, -5, and 5 deg. Test data are presented without analysis
Static and dynamic force tests of a generic fighter configuration designed for sustained supersonic ...
Wind-tunnel data were obtained at a free-stream Mach number of 0.26 for a range of model angle of at...
Spanwise blowing over the wing and canard of a 1:35 model of a close-coupled-canard fighter airplane...
A general research fighter model was tested in the Langley 7 by 10 foot high speed tunnel at a Mach ...
Subsonic lateral-direction and longitudinal characteristics of a forward-swept-wing fighter configur...
A general research fighter model was tested in the Langley 7 by 10-foot high speed tunnel at a Mach ...
A program for the wind tunnel development of underwing leading-edge vortex generators on an NASA sup...
A general research fighter model was tested in the Langley 7- by 10-foot high speed tunnel at a Mach...
The static lateral- and directional-stability characteristics of a high-speed fighter-type airplane,...
A wind-tunnel investigation was made to determine the longitudinal aerodynamic characteristics of a ...
A series of low-speed static wind-tunnel force tests were conducted on a 0.15-scale model of a moder...
The effects of spanwise blowing on two configurations representative of current fighter airplanes we...
The low speed lateral/directional characteristics of a generic 74 degree delta wing body configurati...
A systematic wind tunnel study was conducted in the Langley high-speed 7 by 10 foot tunnel to docume...
A V/STOL tunnel study was performed to determine the effects of spanwise blowing on longitudinal aer...
Static and dynamic force tests of a generic fighter configuration designed for sustained supersonic ...
Wind-tunnel data were obtained at a free-stream Mach number of 0.26 for a range of model angle of at...
Spanwise blowing over the wing and canard of a 1:35 model of a close-coupled-canard fighter airplane...
A general research fighter model was tested in the Langley 7 by 10 foot high speed tunnel at a Mach ...
Subsonic lateral-direction and longitudinal characteristics of a forward-swept-wing fighter configur...
A general research fighter model was tested in the Langley 7 by 10-foot high speed tunnel at a Mach ...
A program for the wind tunnel development of underwing leading-edge vortex generators on an NASA sup...
A general research fighter model was tested in the Langley 7- by 10-foot high speed tunnel at a Mach...
The static lateral- and directional-stability characteristics of a high-speed fighter-type airplane,...
A wind-tunnel investigation was made to determine the longitudinal aerodynamic characteristics of a ...
A series of low-speed static wind-tunnel force tests were conducted on a 0.15-scale model of a moder...
The effects of spanwise blowing on two configurations representative of current fighter airplanes we...
The low speed lateral/directional characteristics of a generic 74 degree delta wing body configurati...
A systematic wind tunnel study was conducted in the Langley high-speed 7 by 10 foot tunnel to docume...
A V/STOL tunnel study was performed to determine the effects of spanwise blowing on longitudinal aer...
Static and dynamic force tests of a generic fighter configuration designed for sustained supersonic ...
Wind-tunnel data were obtained at a free-stream Mach number of 0.26 for a range of model angle of at...
Spanwise blowing over the wing and canard of a 1:35 model of a close-coupled-canard fighter airplane...