Add to ORKGA variable sweep fighter configuration with the wing in the 22 deg sweep position having leading edge slats and trailing edge flaps on the outboard panels was tested at a Mach number of 0.15 in the Langley 7- by 10-foot high speed tunnel. The angle of attack range was 0 deg to 50 deg and the sideslip angle range was -20 deg to 20 deg. Pitch, roll, and yaw control effectiveness were studied as well as the effects of spoilers. The data are presented without analysis
A wind tunnel investigation has been conducted to determine the longitudinal and lateral aerodynamic...
A wind-tunnel investigation was conducted in the Langley 12-Foot Low-Speed Tunnel to study the low-s...
Transonic and supersonic dynamic stability characteristics of variable sweep wing tactical fighter a...
An untwisted wing, which when unswept has an NACA 65-210 section, an aspect ratio of 9.0 and a taper...
A wind-tunnel investigation was conducted in the Langley 12-Foot Low-Speed Tunnel to study the lowsp...
Static stability and control at low subsonic speeds of supersonic aircraft with variable sweep wing
Stability and control of variable sweep wing configuration with outboard wing panels swept back 75 d...
Wind tunnel tests of stability and control of variable sweep wing aircraft at Mach 1.9
An investigation was made in the high Mach number test section of the Langley Unitary Plan wind tunn...
A general research fighter model was tested in the Langley 7- by 10-foot high speed tunnel at a Mach...
An investigation w a s made i n the Langley high-speed 7- by 10-foot tunnel to determine the effect ...
An investigation has been conducted at Mach numbers ranging from 0.06 to 0.94 to determine the effec...
A general research fighter model was tested in the Langley 7 by 10-foot high speed tunnel at a Mach ...
The present investigation was conducted in the Langley high-speed 7-by 10-foot tunnel to determine t...
A preliminary investigation of the static longitudinal and lateral stability characteristics of a 0....
A wind tunnel investigation has been conducted to determine the longitudinal and lateral aerodynamic...
A wind-tunnel investigation was conducted in the Langley 12-Foot Low-Speed Tunnel to study the low-s...
Transonic and supersonic dynamic stability characteristics of variable sweep wing tactical fighter a...
An untwisted wing, which when unswept has an NACA 65-210 section, an aspect ratio of 9.0 and a taper...
A wind-tunnel investigation was conducted in the Langley 12-Foot Low-Speed Tunnel to study the lowsp...
Static stability and control at low subsonic speeds of supersonic aircraft with variable sweep wing
Stability and control of variable sweep wing configuration with outboard wing panels swept back 75 d...
Wind tunnel tests of stability and control of variable sweep wing aircraft at Mach 1.9
An investigation was made in the high Mach number test section of the Langley Unitary Plan wind tunn...
A general research fighter model was tested in the Langley 7- by 10-foot high speed tunnel at a Mach...
An investigation w a s made i n the Langley high-speed 7- by 10-foot tunnel to determine the effect ...
An investigation has been conducted at Mach numbers ranging from 0.06 to 0.94 to determine the effec...
A general research fighter model was tested in the Langley 7 by 10-foot high speed tunnel at a Mach ...
The present investigation was conducted in the Langley high-speed 7-by 10-foot tunnel to determine t...
A preliminary investigation of the static longitudinal and lateral stability characteristics of a 0....
A wind tunnel investigation has been conducted to determine the longitudinal and lateral aerodynamic...
A wind-tunnel investigation was conducted in the Langley 12-Foot Low-Speed Tunnel to study the low-s...
Transonic and supersonic dynamic stability characteristics of variable sweep wing tactical fighter a...