Add to ORKGWind-tunnel results are presented to show the effect of changes in horizontal-tail location on the low-speed static longitudinal stability and steady-state rotary damping in pitch for a complete model with wing and tail surfaces having the quarter-chord lines swept back 45 degrees.NACA TN No. 2381."June 1951."Includes bibliographical references.Wind-tunnel results are presented to show the effect of changes in horizontal-tail location on the low-speed static longitudinal stability and steady-state rotary damping in pitch for a complete model with wing and tail surfaces having the quarter-chord lines swept back 45 degrees.Mode of access: Internet
Low-speed tests of a model with a wing swept back 35 degrees at the 0.33-chord line and a horizontal...
The results of a wind-tunnel investigation of a series of models of nine related horizontal tails ha...
The usual technique of longitudinal stability analysis is adopted but particular attention is paid ...
Wind-tunnel results of the effects of horizontal-tail size and length on the low-speed static longit...
Report presents the results of an investigation conducted in the Langley stability tunnel to determi...
Report presents the results of an investigation conducted in the Langley stability tunnel to determi...
Results are presented of a wind-tunnel investigation to determine influence of the fuselage and tail...
Results are presented of a wind-tunnel investigation to determine influence of the fuselage and tail...
An experimental investigation was made in the Langley stability tunnel to determine whether the low-...
The damping in vaw and the directional stability of a model oscillating in yaw were measured tail-of...
A wind-tunnel investigation has been carried out to determine the static longitudinal stability ad t...
An investigation was made in the Langley gust tunnel of a flexible-wing model with the semichord lin...
The results of an experimental and theoretical investigation of the effects of large artificial vari...
An investigation was made in the LMAL 7- by 10-foot tunnel of the aerodynamic characteristics of a r...
A great majority of present day airplanes are of the low wing cantilever type. An investigation int...
Low-speed tests of a model with a wing swept back 35 degrees at the 0.33-chord line and a horizontal...
The results of a wind-tunnel investigation of a series of models of nine related horizontal tails ha...
The usual technique of longitudinal stability analysis is adopted but particular attention is paid ...
Wind-tunnel results of the effects of horizontal-tail size and length on the low-speed static longit...
Report presents the results of an investigation conducted in the Langley stability tunnel to determi...
Report presents the results of an investigation conducted in the Langley stability tunnel to determi...
Results are presented of a wind-tunnel investigation to determine influence of the fuselage and tail...
Results are presented of a wind-tunnel investigation to determine influence of the fuselage and tail...
An experimental investigation was made in the Langley stability tunnel to determine whether the low-...
The damping in vaw and the directional stability of a model oscillating in yaw were measured tail-of...
A wind-tunnel investigation has been carried out to determine the static longitudinal stability ad t...
An investigation was made in the Langley gust tunnel of a flexible-wing model with the semichord lin...
The results of an experimental and theoretical investigation of the effects of large artificial vari...
An investigation was made in the LMAL 7- by 10-foot tunnel of the aerodynamic characteristics of a r...
A great majority of present day airplanes are of the low wing cantilever type. An investigation int...
Low-speed tests of a model with a wing swept back 35 degrees at the 0.33-chord line and a horizontal...
The results of a wind-tunnel investigation of a series of models of nine related horizontal tails ha...
The usual technique of longitudinal stability analysis is adopted but particular attention is paid ...